CN112591121B - Sensor mounting bracket for helicopter - Google Patents
Sensor mounting bracket for helicopter Download PDFInfo
- Publication number
- CN112591121B CN112591121B CN202110074453.9A CN202110074453A CN112591121B CN 112591121 B CN112591121 B CN 112591121B CN 202110074453 A CN202110074453 A CN 202110074453A CN 112591121 B CN112591121 B CN 112591121B
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- sensor
- plate part
- tail
- mounting bracket
- vibration
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- 238000009434 installation Methods 0.000 claims description 12
- 235000017166 Bambusa arundinacea Nutrition 0.000 claims description 10
- 235000017491 Bambusa tulda Nutrition 0.000 claims description 10
- 241001330002 Bambuseae Species 0.000 claims description 10
- 235000015334 Phyllostachys viridis Nutrition 0.000 claims description 10
- 239000011425 bamboo Substances 0.000 claims description 10
- 238000010276 construction Methods 0.000 claims description 4
- 230000000149 penetrating effect Effects 0.000 claims 1
- 238000004519 manufacturing process Methods 0.000 abstract description 5
- 238000005259 measurement Methods 0.000 abstract description 5
- 230000004075 alteration Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The invention discloses a sensor mounting bracket for a helicopter, which comprises a tail rudder shaft cylinder part, a tail blade, a sensor mounting bracket, a photoelectric sensor, a vibration sensor, a mounting bolt and a connecting cylinder, wherein the tail rudder of the helicopter is provided with the tail rudder shaft cylinder part, the rotation axis of the tail blade is vertical to the central line of the tail rudder shaft cylinder part, a luminous mark is pasted on the tail blade, the photoelectric sensor and the vibration sensor are mounted on the tail rudder shaft cylinder part through the sensor mounting bracket, and the sensor mounting bracket is mounted on the tail rudder shaft cylinder part through the mounting bolt and the connecting cylinder, and the sensor mounting bracket is characterized in that: a sensor mounting support is formed by a photoelectric sensor mounting support and a vibration sensor mounting support, and the light direction of the photoelectric sensor is vertical to the axis direction of the vibration sensor. The vibration measuring device is simple in structure, convenient and simple to install, replace and maintain, accurate in vibration measurement and rotating speed information, few in structure, convenient and fast to combine and convenient to produce and manufacture.
Description
Technical Field
The invention relates to the technical field of sensor installation/measurement for helicopters, in particular to a sensor installation bracket for a helicopter.
Background
In the existing sensor mounting bracket for the helicopter, firstly, a photoelectric sensor and a vibration sensor are separately mounted on different mounting brackets, and the structural arrangement is unreasonable; secondly, the photoelectric sensor and the vibration sensor are combined on a combined mounting bracket, but the combined mounting bracket has a complex structure and is inconvenient to mount and maintain.
Disclosure of Invention
The invention aims to overcome the defects in the prior art, and provides a sensor mounting bracket for a helicopter, which has the advantages of simple structure, convenience and simplicity in installation, replacement and maintenance, accurate vibration and rotating speed information measurement, few structures, convenience and quickness in combination and convenience in production and manufacturing.
In order to achieve the purpose, the invention adopts the technical scheme that:
the utility model provides a sensor installing support for helicopter, it includes tail rudder axle section of thick bamboo portion (1), tail rotor blade (2), sensor installing support (3), photoelectric sensor (6), vibration sensor (7), construction bolt (8), connecting cylinder (9), the tail rudder of helicopter has tail rudder axle section of thick bamboo portion, the rotation axis of tail paddle leaf is perpendicular with the central line of tail rudder axle section of thick bamboo portion, it has luminous mark (21) to paste on the tail paddle leaf, there is photoelectric sensor, vibration sensor through sensor installing support installation in the tail rudder axle section of thick bamboo portion, the sensor installing support passes through construction bolt (8), connecting cylinder (9) are installed in tail rudder axle section of thick bamboo portion, its characterized in that: a sensor mounting bracket is formed by a photoelectric sensor mounting bracket and a vibration sensor mounting bracket, and the light direction of the photoelectric sensor (6) is vertical to the axial direction of the vibration sensor (7).
Further, the photosensor mounting support (4) comprises a first plate portion (41), a second plate portion (42), a first mounting hole (43), and a second mounting hole (44), wherein the first plate portion is arranged perpendicular to the second plate portion, the first plate portion is provided with the first mounting hole, and the second plate portion is provided with the second mounting hole.
Further, the vibration sensor mounting support (5) comprises a fourth plate portion (51), a fifth plate portion (52), a sixth plate portion (53), a seventh plate portion (54), a threaded connection ring (55) and a fixing hole (56), wherein the fourth plate portion is arranged perpendicular to the fifth plate portion, the fifth plate portion and the sixth plate portion are arranged in parallel, the seventh plate portion is arranged below the fourth plate portion, two sides of the seventh plate portion are respectively connected with the fifth plate portion and the sixth plate portion, the threaded connection ring is arranged on one side face of the fourth plate portion, the threaded connection ring is provided with a first internal threaded hole, and the seventh plate portion is provided with the fixing hole.
Furthermore, adopt the nut to install on first board (41) after first mounting hole (43) is passed to the one end of photoelectric sensor (6), the one end of vibration sensor (7) passes second mounting hole (44), threaded connection ring (55) and with this first internal thread hole threaded connection in proper order, threaded connection ring has both realized installing vibration sensor erection support on photoelectric sensor erection support, has realized installing vibration sensor on photoelectric sensor erection support again.
Furthermore, the connecting cylinder (9) is provided with a second internal threaded hole, one end of the connecting cylinder is provided with an external thread section, the external thread section is screwed in the threaded hole on the tail rudder shaft cylinder part, the other end of the connecting cylinder is provided with a step part, the step part is matched in the fixing hole (56), and the mounting bolt (8) penetrates through the fixing hole of the seventh plate part (54) and then is in threaded connection with the second internal threaded hole of the connecting cylinder.
Further, the axial direction of the vibration sensor (7) is consistent with the central line direction of the tail rudder shaft barrel part (1) and is used for measuring the radial vibration of the helicopter; the light direction of the photoelectric sensor (6) is consistent with the rotation axis direction of the tail paddle (2).
According to the sensor mounting bracket for the helicopter, the threaded connecting ring not only realizes mounting of the vibration sensor mounting bracket on the photoelectric sensor mounting bracket, but also realizes mounting of the vibration sensor on the photoelectric sensor mounting bracket, the vibration sensor and the photoelectric sensor are ingeniously mounted/fixed on one mounting bracket, and the position relation is just the vertical direction (the light direction of the photoelectric sensor is vertical to the axial direction of the vibration sensor); the mounting bolt penetrates through the fixing hole of the seventh plate part and then is in threaded connection with the second internal threaded hole of the connecting cylinder, one end of the connecting cylinder is provided with an external threaded section, and the external threaded section is screwed in the threaded hole in the cylinder part of the tail rudder shaft. The vibration measuring device is simple in structure, convenient and simple to install, replace and maintain, accurate in vibration measurement and rotating speed information, few in structure, convenient and fast to combine and convenient to produce and manufacture.
Drawings
FIG. 1 is a schematic structural view of a sensor mounting bracket for a helicopter in accordance with the present invention;
FIG. 2 is a schematic structural view of a sensor mounting bracket for a helicopter in accordance with the present invention;
FIG. 3 is a schematic structural view of a sensor mounting bracket for a helicopter in accordance with the present invention;
FIG. 4 is a schematic structural view of a sensor mounting bracket for a helicopter in accordance with the present invention;
FIG. 5 is a schematic view of a sensor mounting bracket for a helicopter of the present invention;
FIG. 6 is a schematic view of the mounting bracket of the present invention;
fig. 7 is a schematic view of the mounting bracket structure of the present invention.
In the figure: the rear rudder shaft tube part 1, the rear propeller blade 2, the light emitting mark 21, the sensor mounting bracket 3, the photoelectric sensor mounting bracket 4, the first plate part 41, the second plate part 42, the first mounting hole 43, the second mounting hole 44, the vibration sensor mounting bracket 5, the fourth plate part 51, the fifth plate part 52, the sixth plate part 53, the seventh plate part 54, the threaded connection ring 55, the fixing hole 56, the photoelectric sensor 6, the vibration sensor 7, the mounting bolt 8, and the connection tube 9.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in fig. 1-7, a sensor mounting bracket for a helicopter, which comprises a tail rudder shaft tube part 1, a tail rotor blade 2, a sensor mounting bracket 3, a photoelectric sensor 6, a vibration sensor 7, a mounting bolt 8 and a connecting tube 9, wherein the tail rudder of the helicopter is provided with the tail rudder shaft tube part 1, the rotation axis of the tail rotor blade 2 is perpendicular to the center line of the tail rudder shaft tube part 1, a light emitting mark 21 is adhered on the tail rotor blade 2, the photoelectric sensor 6 and the vibration sensor 7 are mounted on the tail rudder shaft tube part 1 through the sensor mounting bracket 3, the sensor mounting bracket 3 is mounted on the tail rudder shaft tube part 1 through the mounting bolt 8 and the connecting tube 9, and the sensor mounting bracket is characterized in that: a sensor mounting bracket 3 is formed by a photoelectric sensor mounting support 4 and a vibration sensor mounting support 5, and the light direction of a photoelectric sensor 6 is vertical to the axial direction of a vibration sensor 7.
As shown in fig. 6 to 7, the photosensor mount holder 4 includes a first plate portion 41, a second plate portion 42, a first mounting hole 43, and a second mounting hole 44, the first plate portion 41 being disposed perpendicular to the second plate portion 42, the first plate portion 41 having the first mounting hole 43, the second plate portion 42 having the second mounting hole 44.
The vibration sensor mounting bracket 5 includes a fourth plate portion 51, a fifth plate portion 52, a sixth plate portion 53, a seventh plate portion 54, a threaded connection ring 55, and a fixing hole 56, the fourth plate portion 51 is disposed perpendicular to the fifth plate portion 52, the fifth plate portion 52 is disposed parallel to the sixth plate portion 53, the seventh plate portion 54 is disposed/connected below the fourth plate portion 51, both sides of the seventh plate portion 54 are connected to the fifth plate portion 52 and the sixth plate portion 53, respectively, the threaded connection ring 55 is disposed on one side surface of the fourth plate portion 51, the threaded connection ring 55 has a first internal threaded hole, and the fixing hole 56 is disposed on the seventh plate portion 54.
One end of the photoelectric sensor 6 passes through the first mounting hole 43 and then is mounted on the first plate portion 41 by using a nut, one end of the vibration sensor 7 sequentially passes through the second mounting hole 44 and the threaded connection ring 55 and is in threaded connection with the first internal threaded hole, the threaded connection ring 55 not only realizes mounting of the vibration sensor mounting support 5 on the photoelectric sensor mounting support 4, but also realizes mounting of the vibration sensor 7 on the photoelectric sensor mounting support 4, the vibration sensor 7 and the photoelectric sensor 6 are ingeniously mounted/fixed on one mounting bracket 3, and the position relation is just the vertical direction (the light direction of the photoelectric sensor 6 is perpendicular to the axial direction of the vibration sensor 7).
As shown in fig. 3 to 7, the joint cylinder 9 has a second female screw hole, one end of the joint cylinder 9 has a male screw section which is screwed into the screw hole of the rudder shaft cylinder 1, the other end of the joint cylinder 9 has a stepped portion which is fitted into the fixing hole 56, and the mounting bolt 8 is screwed into the second female screw hole of the joint cylinder 9 after passing through the fixing hole 56 of the seventh plate portion 54.
The combined mounting bracket 3 of the photoelectric sensor 6 and the vibration sensor 7 is mounted on a tail speed reducer/tail rudder shaft barrel part 1 of the helicopter, the photoelectric sensor is mounted/fixed on a photoelectric sensor support 4, the vibration sensor is fixed on a vibration sensor support 5, and the axial direction of the vibration sensor 7 points to the right back of the helicopter or is consistent/repeated with the central line direction of the tail rudder shaft barrel part 1 and is used for measuring the radial vibration of the helicopter. The vibration sensor 7 measures the radial vibration caused by the tail blade, that is, the vibration value of the circumference formed by one rotation of the tail blade in the axial direction.
The photoelectric sensor 6 is right opposite to the rotating direction of the tail blades 2, one tail blade is pasted with a reflecting mark 21, and the rotating speed of the tail blade is calculated by sensing the speed of the reflecting mark through one rotation of the tail blade; and after the rotating speed of the tail blade is stable, measuring the vibration value.
The direction of the photoelectric sensor 6 is over against the cursor of the tail rotor blade, so that the reflecting target is ensured to be correctly adhered and aligned with the photoelectric sensor. After all the installed components are fixed, the cables are bundled into a bundle and connected with a reading meter to read the vibration value. The vibration sensor and the photoelectric sensor are ingeniously fixed on one mounting bracket, and the position relation is exactly the vertical direction.
According to the sensor mounting bracket for the helicopter, the threaded connecting ring 55 not only realizes mounting of the vibration sensor mounting bracket 5 on the photoelectric sensor mounting bracket 4, but also realizes mounting of the vibration sensor 7 on the photoelectric sensor mounting bracket 4, the vibration sensor 7 and the photoelectric sensor 6 are ingeniously mounted/fixed on one mounting bracket 3, and the position relation is just the vertical direction (the light direction of the photoelectric sensor 6 is vertical to the axial direction of the vibration sensor 7); the mounting bolt 8 is screwed into the second female screw hole of the joint cylinder 9 after passing through the fixing hole 56 of the seventh plate portion 54, and one end of the joint cylinder 9 has a male screw section which is screwed into the screw hole of the rudder trunk portion 1. The vibration measuring device is simple in structure, convenient and simple to install, replace and maintain, accurate in vibration measurement and rotating speed information, few in structure, convenient and fast to combine and convenient to produce and manufacture.
The above-described embodiments are illustrative of the present invention and not restrictive, it being understood that various changes, modifications, substitutions and alterations can be made herein without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.
Claims (3)
1. The utility model provides a sensor installing support for helicopter, it includes tail rudder axle section of thick bamboo portion (1), tail rotor blade (2), sensor installing support (3), photoelectric sensor (6), vibration sensor (7), construction bolt (8), connecting cylinder (9), the tail rudder of helicopter has tail rudder axle section of thick bamboo portion, the rotation axis of tail paddle leaf is perpendicular with the central line of tail rudder axle section of thick bamboo portion, it has luminous mark (21) to paste on the tail paddle leaf, there is photoelectric sensor, vibration sensor through sensor installing support installation in the tail rudder axle section of thick bamboo portion, the sensor installing support passes through construction bolt (8), connecting cylinder (9) are installed in tail rudder axle section of thick bamboo portion, its characterized in that: a sensor mounting bracket is formed by a photoelectric sensor mounting bracket and a vibration sensor mounting bracket, and the light direction of a photoelectric sensor (6) is vertical to the axial direction of a vibration sensor (7); the photoelectric sensor mounting support (4) comprises a first plate part (41), a second plate part (42), a first mounting hole (43) and a second mounting hole (44), wherein the first plate part and the second plate part are arranged perpendicularly, the first plate part is provided with the first mounting hole, and the second plate part is provided with the second mounting hole; the vibration sensor mounting support (5) comprises a fourth plate part (51), a fifth plate part (52), a sixth plate part (53), a seventh plate part (54), a threaded connecting ring (55) and a fixing hole (56), wherein the fourth plate part is arranged perpendicular to the fifth plate part, the fifth plate part and the sixth plate part are arranged in parallel, the seventh plate part is arranged below the fourth plate part, two sides of the seventh plate part are respectively connected with the fifth plate part and the sixth plate part, the threaded connecting ring is arranged on one side surface of the fourth plate part, the threaded connecting ring is provided with a first internal threaded hole, and the seventh plate part is provided with the fixing hole; one end of the photoelectric sensor (6) is installed on the first plate portion (41) through a nut after penetrating through the first installation hole (43), one end of the vibration sensor (7) sequentially penetrates through the second installation hole (44) and the threaded connection ring (55) and is in threaded connection with the first internal threaded hole, and the threaded connection ring not only realizes installation of the vibration sensor installation support on the photoelectric sensor installation support, but also realizes installation of the vibration sensor on the photoelectric sensor installation support.
2. A sensor mounting bracket for a helicopter according to claim 1 wherein said connector barrel (9) has a second internally threaded bore, one end of the connector barrel has an externally threaded section which is threaded into the threaded bore in the barrel portion of the tail rotor shaft, the other end of the connector barrel has a stepped portion which fits into the fixing bore (56), and the mounting bolt (8) is threaded into the second internally threaded bore of the connector barrel after passing through the fixing bore of the seventh plate portion (54).
3. A sensor mounting bracket for a helicopter according to claim 2, characterized in that the axial direction of said vibration sensor (7) coincides with the direction of the centre line of the rudder shaft section (1) for measuring the radial vibration of the helicopter; the light direction of the photoelectric sensor (6) is consistent with the rotation axis direction of the tail paddle (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110074453.9A CN112591121B (en) | 2021-01-20 | 2021-01-20 | Sensor mounting bracket for helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110074453.9A CN112591121B (en) | 2021-01-20 | 2021-01-20 | Sensor mounting bracket for helicopter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN112591121A CN112591121A (en) | 2021-04-02 |
| CN112591121B true CN112591121B (en) | 2022-04-22 |
Family
ID=75207274
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110074453.9A Active CN112591121B (en) | 2021-01-20 | 2021-01-20 | Sensor mounting bracket for helicopter |
Country Status (1)
| Country | Link |
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| CN (1) | CN112591121B (en) |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5527004A (en) * | 1993-02-24 | 1996-06-18 | Helix Air, Inc. | Control system for aircraft |
| EP2576344A2 (en) * | 2010-05-26 | 2013-04-10 | Lord Corporation | Real time active helicopter vibration control and rotor track and balance systems |
| FR2988075B1 (en) * | 2012-03-19 | 2014-04-25 | Eurocopter France | DEVICE FOR MONITORING THE BEHAVIOR AND / OR TRAINING BEHAVIOR OF A ROTOR BLADE OF A GIRAVION |
| KR101369212B1 (en) * | 2012-08-01 | 2014-03-27 | 한국과학기술원 | Laser ultrasonic imaging of a rotating blade |
| US10424134B2 (en) * | 2016-08-17 | 2019-09-24 | Bell Helicopter Textron Inc. | Diagnostic method, system and device for a rotorcraft drive system |
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2021
- 2021-01-20 CN CN202110074453.9A patent/CN112591121B/en active Active
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| Publication number | Publication date |
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| CN112591121A (en) | 2021-04-02 |
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Address after: 333000 No.01 Zhihang Road, Jingdezhen high tech Zone, Jingdezhen City, Jiangxi Province Patentee after: Jiangxi Helicopter Co.,Ltd. Address before: 333000 No.01 Zhihang Road, Jingdezhen high tech Zone, Jingdezhen City, Jiangxi Province Patentee before: BGAC JIANGXI HELICOPTER CO.,LTD. |
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