KR20120138541A - Sensor and wiring equipped method for detecting rotor blade of rotary-wing aircraft - Google Patents

Sensor and wiring equipped method for detecting rotor blade of rotary-wing aircraft Download PDF

Info

Publication number
KR20120138541A
KR20120138541A KR1020110058100A KR20110058100A KR20120138541A KR 20120138541 A KR20120138541 A KR 20120138541A KR 1020110058100 A KR1020110058100 A KR 1020110058100A KR 20110058100 A KR20110058100 A KR 20110058100A KR 20120138541 A KR20120138541 A KR 20120138541A
Authority
KR
South Korea
Prior art keywords
rotor blade
magnet wire
measurement sensor
sensor
mounting
Prior art date
Application number
KR1020110058100A
Other languages
Korean (ko)
Inventor
하해용
노병찬
Original Assignee
한국항공우주산업 주식회사
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 한국항공우주산업 주식회사 filed Critical 한국항공우주산업 주식회사
Priority to KR1020110058100A priority Critical patent/KR20120138541A/en
Publication of KR20120138541A publication Critical patent/KR20120138541A/en

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/006—Safety devices
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B7/00—Measuring arrangements characterised by the use of electric or magnetic techniques
    • G01B7/16—Measuring arrangements characterised by the use of electric or magnetic techniques for measuring the deformation in a solid, e.g. by resistance strain gauge
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D2045/0085—Devices for aircraft health monitoring, e.g. monitoring flutter or vibration

Abstract

PURPOSE: A sensor for measuring a rotor blade of a rotorcraft and a method for mounting a wire are provided to reduce damage to a wire and to solve problems due to the poor contact of a soldering part between a flat cable and a magnet wire. CONSTITUTION: A sensor for measuring a rotor blade of a rotorcraft and a method for mounting a wire are as follows. The paint on the surface of a rotor blade is removed(S1). A magnet wire and a sensor are mounted on the surface of the rotor blade(S2). The terminal of the sensor and the terminal of the magnet wire are soldered(S3). A coating layer for protecting the sensor and the magnet wire is formed(S5). [Reference numerals] (S1) Step for removing paint; (S2) Step for mounting a magnet wire and a measuring sensor; (S3) Step for soldering; (S5) Step for forming a coating layer

Description

Sensor and wiring equipped method for detecting rotor blade of rotary-wing aircraft}

The present invention relates to a rotor blade measuring sensor and a wiring mounting method of a rotorcraft, and more particularly, the rotor blade measuring sensor and a magnet wire, which are mounted to grasp deformation of the rotor blade and the like, are stably mounted. It relates to a rotor blade measurement sensor and wiring mounting method of a rotorcraft aircraft that its durability can be improved.

In general, a rotorcraft aircraft is propelled by the lift generated by rotating the rotor blades. In particular, a rotorcraft aircraft such as a helicopter can use the power of a fossil fuel engine to rotate the rotor blades installed at the upper part of the fuselage at high speed to perform vertical ascending and descending flight and stationary flight, which is impossible in a fixed wing aircraft.

5 shows a schematic external perspective view of a helicopter, which is a type of rotary wing aircraft. The main rotor blade (Main rotor blade) (120a) is installed on the upper body 110 of the helicopter 100, the tail rotor blade (tail rotor blade) (120b) is installed on the tail portion of the fuselage (110) ) Is installed.

The main rotor blade 120a provides the driving force of the vertical lift and forward flight of the helicopter 100, and the tail rotor blade 120b maintains the stance of the fuselage 110 stably during flight of the helicopter 100.

The prototype of a rotorcraft aircraft having such a configuration is provided with a measurement sensor such as a main rotor blade and a tail rotor blade and configured to measure strain and load of the structure.

However, in a region where rotation and up, down, left, and right movements are severely generated, such as the rotor blade 120, durability problems may occur due to the behavior of the blade when the measurement sensor or the test wiring is installed.

Looking at the case of performing a flight test by mounting a flat cable (200) and the measurement sensor 300 to the main rotor blade (120a) as an example, conventionally connected to the measurement sensor as shown in Figs. As a wiring, a flat cable and a magnet wire were used. More specifically, after removing the paint on the surface of the main rotor blade (120a), by applying an adhesive to form an adhesive layer 400, and after bonding the flat cable 200, the measurement sensor 300 terminal and the flat cable 200 Was soldered so that a bridge circuit could be formed using the magnet wire 500. Then, in order to protect the flat cable 200, the measurement sensor and the soldering portion, the coating layer 600 is formed through an adhesive, and then the top layer is coated with paint or a surface protector to form the protective layer 700. Formed and finished.

However, if the measurement sensor is installed in this way, the rotor cable and the rotor's dynamic characteristics are not sufficiently secured during flight test operation. Therefore, the flat cable itself is damaged, and the contact point is poor at the soldered part 510 of the flat cable and the magnet wire. There was a problem that only the durability strength of about 3 to 6 months and the like occurs.

In addition, due to such defects and damages, the replacement of measuring sensors, materials, etc. is performed for about one month, resulting in a problem in the schedule and a huge loss in the cost of parts and manpower used during the replacement. there was.

The present invention is to solve the above problems,

Sensor for measuring rotor blades of rotorcraft that can prevent damage and prolong the replacement time by increasing rotor blade rotation and the durability of the aircraft's dynamic characteristics when installing measurement sensors or wires connected to rotor blades of rotorcraft; It is an object to provide a wiring mounting method.

Another object of the present invention is to allow the mounted magnet wire to effectively cope with the up, down, left and right movement of the rotor blade.

Still another object of the present invention is to prevent malfunction by checking for defects in advance.

Another object of the present invention is to maintain the aerodynamic characteristics of the rotor blades.

The present invention to achieve the above object,

Removing paint on the rotor blade surface;

Mounting a magnet wire and a measurement sensor on the surface of the rotor blade from which the paint is removed;

Soldering the measurement sensor terminal and the terminal of the magnet wire;

It provides a rotor blade measurement sensor and wiring mounting method for a rotorcraft aircraft comprising the step of forming a coating layer for protecting the measurement sensor and the magnet wire.

In addition, in the step of mounting the magnet wire and the measurement sensor, the magnet wire is characterized in that the mounting by giving a slack at some point.

In addition, it characterized in that it further comprises the step of checking whether the operation before the coating layer is formed normally.

In addition, the total thickness of the coating layer is characterized in that less than 1mm.

In addition, the mounting position of the magnet wire is characterized in that the mounting in consideration of the aerodynamic demand.

As described above, when the rotor blade measurement sensor and wiring mounting method of the rotorcraft according to the present invention are used, the measurement sensor and the wiring do not use the flat cable which was easy to be damaged due to the wide contact area with the rotor blade. The rate is reduced, and mounting can be simplified by simply bending and bypassing the magnet wire without soldering to connect the magnet wire to the conventional flat cable, and there is no soldering portion between the flat cable and the magnet wire. Its durability is improved by eliminating problems caused by contact failures of these soldering parts during flight, which can delay the replacement time of measurement sensors and materials, thus reducing the loss of time, manpower, and cost for remounting. It has a significant reducing effect.

In addition, it is possible to flexibly cope with the up, down, left and right movements of the rotor blades by giving a slack when the magnet wire is mounted, thereby improving the durability of the wiring and making it possible to use it for a long time.

In addition, by checking after the installation work of the magnet wire and the measurement sensor, it is possible to grasp in advance whether the installation work is performed correctly, thus detecting the malfunction of the measurement sensor after the completion of the installation work, thereby reducing the trouble of additional work. The work can be performed.

In addition, by installing the magnet wire in consideration of the aerodynamic demands of the rotor blades and limiting the thickness of the coating layer for protecting the magnet wire and the measurement sensor, the aerodynamic force required for the rotor blade despite the mounting of the magnet wire and measurement sensor or the formation of the coating layer. The purpose is to maintain the performance without changing or deteriorating characteristics.

1 is a flow chart showing a rotor blade measurement sensor and wiring mounting method of a rotorcraft according to an embodiment of the present invention.
Figure 2 is a perspective view showing a state attached to the measurement sensor and the magnet wire.
Figure 3 is a front view showing the appearance of the rotor blade with a coating layer formed.
Figure 4 is a flow chart showing a rotor blade measuring sensor and wiring mounting method of a rotorcraft according to another embodiment of the present invention.
5 is a schematic external perspective view of a typical helicopter.
6 is a cross-sectional view showing a mounting state of a conventional measurement sensor.
7 is a perspective view showing a conventional measurement sensor and the wiring state.

Hereinafter, the present invention will be described in detail with reference to the embodiments shown in the accompanying drawings, but the present invention is not limited to the embodiments shown in the drawings.

1 is a flowchart illustrating a rotor blade measuring sensor and a wire mounting method of a rotorcraft according to the present invention, Figure 2 is a perspective view showing the mounting of the measurement sensor and the magnet wire, Figure 3 is a rotor blade of the coating layer is formed Front view showing the state.

As shown in FIG. 1, the present invention first performs a step S1 of removing paint on the surface of the rotor blade 120.

Removing the paint is intended to prevent the rotor blade 120 from thickening due to the thickening of the rotor blades 120 when the coating layer is applied later, and another purpose is that a magnet wire or a protective coating agent is applied to the surface of the blade. In order to bond more strongly.

At this time, the removal position of the paint on the rotor blade 120 is performed in consideration of the mounting position of the measurement sensor and the mounting position of the magnet wire 10.

The next step is to perform the step (S2) of mounting the magnet wire 10 and the measurement sensor on the rotor blade surface 120c from which the paint has been removed.

Here, the measurement sensor is for measuring the strain and load of the rotor blade, strain gage (Strain gage) may be preferably used. This strain gauge causes the electrical resistance of the strain gage to change when the structure is deformed, thereby measuring the strain of the rotor blades and ultimately measuring the load. At this time, the measurement sensor is mounted based on the sensor mounting requirements of the rotor blade.

The magnet wire 10 is mounted to surround the rotor blades 120 to form a bridge circuit. When the micro wires are deformed due to the magnet wires 10 mounted in this way, the electric current of the magnet wires that are electrically balanced. As the flow changes, the sensor can identify the deformation of the rotor blades. In addition, since some of the magnet wires 11 connected to the terminal are mounted by bypassing the rotor blades 120 in accordance with the bridge circuit diagram, a separate circuit for forming a bridge circuit in a conventional flat cable is provided. There is no need to solder and mount the magnet wires, making the operation simpler.

At this time, the magnet wire 10 is preferably mounted in consideration of the aerodynamic requirements of the rotor blades. Aerodynamic requirements are the minimum aerodynamic characteristics required for the rotor blades.As a result of the aerodynamic demands, the aerodynamic characteristics required for the blades may appear sufficiently in spite of the magnet wires. You can prevent it.

When the magnet wire is caught, it may be temporarily attached to the surface of the blade through the adhesive means 20 including an adhesive or an adhesive tape.

In addition, the magnet wire 10 may be mounted by giving a slack 13 at some point.

This is to give a margin to the magnet wire 10 mounted on the rotor blade 120 to be able to flexibly cope with the up, down, left, right movement of the rotor blade, as shown in Figure 2 wavy slack Can be processed.

The formation of the slack 13 has the effect of further improving the durability of the magnet wire mounted on the rotor blade, that is, the wiring during the flight test, so that it can be used for a long time.

The next step is to solder the measurement sensor terminal and the terminal of the magnet wire (S3). Through this step, the measurement sensor and the magnet wire are connected so that the measurement sensor can recognize the change in the resistance value indicated by the structure deformation and measure the strain.

Finally, forming a coating layer 30 for protecting the measurement sensor and the magnet wire (S5). This is to prevent the measurement sensor and the magnet wire from being damaged or separated from the rotor blades due to external factors. As shown in FIG.

However, it is preferable that the coating layer 30 has a total thickness of 1 mm or less.

If the thickness of the coating layer 30 exceeds 1mm, as the thickness of the rotor blades is thickened, the aerodynamic characteristics required for the rotor blades may be changed or degraded, making it difficult to achieve the desired performance.

In addition, although not shown in the drawings, it is possible to form a protective layer by top coating with a paint or coating as in the prior art, thereby protecting the surface of the rotor blades and more effectively protecting the wiring and measurement sensors mounted on the rotor blades. have.

The measurement sensor and the wiring of the rotor blades of the rotor blades mounted in the above-described manner do not use a flat cable which is easy to be damaged due to the wide contact area with the rotor blades, thereby reducing the breakage rate of the wiring, and the magnet wire in the conventional flat cable. Installation can be simplified by simply bending and bypassing the magnet wire without soldering to connect the wires.There is no soldering part between the flat cable and the magnet wire. Its durability can be solved such that problems can be solved, which can delay the replacement of measurement sensors and materials, thereby significantly reducing the loss of time, manpower, and cost for remounting.

4 is a flowchart illustrating a rotor blade measuring sensor and a wire mounting method of a rotorcraft according to another embodiment of the present invention.

As shown therein, the present invention may further include a step (S4) of checking whether the operation is normally performed before forming the coating layer.

This is to determine in advance whether the mounting operation of the magnet wire is correctly performed so as not to replace the magnet wire or measuring sensor after the formation of the coating layer.

In this way, by checking the operation status in advance and confirming the operation, it is possible to perform the installation work more efficiently since the malfunction of the measuring sensor is detected after the completion of the mounting work and no additional work such as replacement and repair is performed.

120: rotor blade
120c: rotor blade surface without paint
10: magnet wire
11: some magnet wire
13: slack
20: bonding means
30: coating layer

Claims (5)

Removing the paint on the rotor blade surface (S1);
Mounting the magnet wire and the measurement sensor on the surface of the rotor blade from which the paint is removed (S2);
Soldering the measurement sensor terminal and the terminal of the magnet wire (S3);
Rotor blade measurement sensor and wiring mounting method of a rotorcraft aircraft comprising the step (S5) of forming a coating layer for protecting the measurement sensor and the magnet wire. The method according to claim 1,
In the step of mounting the magnet wire and the measurement sensor (S2), the magnet wire (10) is a rotor blade measuring sensor and wiring mounting method of the rotorcraft, characterized in that the mounting portion given a slack (13) at some point. The method according to claim 2,
The rotor blade measurement sensor and wiring mounting method of the rotor blade aircraft, characterized in that it further comprises the step (S4) of checking whether the operation before the coating layer 30 is formed normally. The method according to claim 3,
Rotor blade measurement sensor and wiring mounting method of the rotorcraft, characterized in that the total thickness of the coating layer 30 to be 1mm or less. The method of claim 4,
Rotor blade measurement sensor and wiring mounting method of a rotorcraft, characterized in that the mounting position of the magnet wire is mounted in consideration of the aerodynamic requirements.
KR1020110058100A 2011-06-15 2011-06-15 Sensor and wiring equipped method for detecting rotor blade of rotary-wing aircraft KR20120138541A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1020110058100A KR20120138541A (en) 2011-06-15 2011-06-15 Sensor and wiring equipped method for detecting rotor blade of rotary-wing aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020110058100A KR20120138541A (en) 2011-06-15 2011-06-15 Sensor and wiring equipped method for detecting rotor blade of rotary-wing aircraft

Publications (1)

Publication Number Publication Date
KR20120138541A true KR20120138541A (en) 2012-12-26

Family

ID=47905322

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1020110058100A KR20120138541A (en) 2011-06-15 2011-06-15 Sensor and wiring equipped method for detecting rotor blade of rotary-wing aircraft

Country Status (1)

Country Link
KR (1) KR20120138541A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20170006451A (en) * 2015-07-08 2017-01-18 세메스 주식회사 Priming unit and Apparatus for coating chemical having the same
KR20190103531A (en) 2018-02-14 2019-09-05 한국기계연구원 Method for manufacturing metal parts embedded with electronic components and electronic components embedded metal part manufactured by the method
KR20200065304A (en) 2018-11-30 2020-06-09 한국기계연구원 A metal part comprising electronic components with non-continuous microstructure layer and its manufacturing method
KR20230101028A (en) 2021-12-29 2023-07-06 울산과학기술원 Intelligent digital metal parts and manufacturing method thereof, Artificial intelligence system including the same

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20170006451A (en) * 2015-07-08 2017-01-18 세메스 주식회사 Priming unit and Apparatus for coating chemical having the same
KR20190103531A (en) 2018-02-14 2019-09-05 한국기계연구원 Method for manufacturing metal parts embedded with electronic components and electronic components embedded metal part manufactured by the method
KR20200065304A (en) 2018-11-30 2020-06-09 한국기계연구원 A metal part comprising electronic components with non-continuous microstructure layer and its manufacturing method
KR20230101028A (en) 2021-12-29 2023-07-06 울산과학기술원 Intelligent digital metal parts and manufacturing method thereof, Artificial intelligence system including the same

Similar Documents

Publication Publication Date Title
KR20120138541A (en) Sensor and wiring equipped method for detecting rotor blade of rotary-wing aircraft
CN104359393B (en) A kind of strain gauge and its manufacture and installation method
US10626849B2 (en) Methods, systems, and devices for tether core diagnostics and monitoring
CN103630285B (en) Near space vehicle RCS Jet enterference power and disturbance torque measurement mechanism
US20090324409A1 (en) Rotor blade monitoring
JP2017151018A (en) Inspection method of windmill receptor
CN106525385B (en) Model integrated horizontal vertical tail aerodynamic force measuring device
US20110138901A1 (en) Method of wind tunnel measurement of airfoil
JP6336720B2 (en) Wrapped strain gauge for brake rod
US20100000066A1 (en) Method for assembling de-icing matting and a metal shield on a structure
JP2011158472A (en) Method of attaching load sensor on surface of rotor blade, and the rotor blade
KR20160027529A (en) Method for testing fatigue life of composit airfoil structure
CN109059747A (en) A kind of temporary frame work wire grid formula high temperature strain gauge and its manufacture and use method
CN110186634B (en) Heat load fatigue test method for helicopter rotor blade deicing-preventing electric heating assembly
CN105280859A (en) Collision protection structure of battery system of electric vehicle, assembling method and detaching method for collision protection structure
CN105241590A (en) Method for testing dynamic stress of rocker arm of air bleeding band under running state, and strain gauge fixing device
US11867155B2 (en) Method for providing a wind turbine blade with lightning protection and a wind turbine blade
CN205209733U (en) Torgue measurement balance
CN115950639B (en) Dynamic stress test line switching method for disc separation fan rotor blade
CN114112405B (en) Multimode mechanical sensor for aeroengine and preparation method
CN105370508A (en) Electromagnetic shielding of a strain gauge in a wind power installation
CN114279586A (en) Engine blade film temperature sensor and preparation method thereof
CN114354033A (en) Force sensor and manufacturing method thereof
CN113405509A (en) Method for measuring conductor sag of power transmission line based on unmanned aerial vehicle
CN111731503A (en) Connection method of transmission interface of embedded sensor for rotor blade and rotor blade

Legal Events

Date Code Title Description
A201 Request for examination
E601 Decision to refuse application