KR101607083B1 - Outer mounted apparatus for obtaining vibration data of military Aircraft and Control method thereof - Google Patents

Abstract

The present invention relates to a vibration data collection technology of an aircraft in flight and, more specifically, relates to an outer mounted measuring apparatus and a method, wherein the apparatus is mounted on an armed mounting stand of a military aircraft to measure vibration generated in a wing and a neighboring mounting object with an acceleration sensor and an image sensor, thereby storing acceleration data and image data. The outer mounted measuring apparatus comprises: a measuring sensor measuring acceleration sensor data, stereo image data, flight information data, time data, and temperature sensor data of the military aircraft; a data measuring device storing the acceleration sensor data, GPS data, the time data, and the temperature sensor data; an image measuring device storing the image data; and a power supply signal distribution device mounted on the armed mounting stand of the military aircraft.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to an external mounted measuring instrument for acquiring vibration data of a military aircraft,

More particularly, the present invention relates to a technique for collecting vibration data of an airplane during flight, and more particularly, to a vibration data collecting technique of an airplane during flight, which is mounted on a military aircraft arming mount and measures vibration generated in a wing and neighboring mounts using an acceleration sensor and an image sensor, And an external mounted measuring instrument and method for storing data and image data.

Exterior attachments to the aircraft affect load, vibration and dynamic characteristics, flight stability, and performance of the aircraft. Therefore, the fitting suitability must be confirmed in advance before operating the new fitting. Particularly, even if a previously proven installation has a different combination shape, the existing test and / or certification result can not be applied as it is, and the certification process through separate analysis and / or testing must be performed.

From an aerodynamic standpoint, the suitability of an external mount for mounting must be demonstrated in terms of load, dynamic characteristics and / or durability. Aerodynamic impacts and / or durability of these should be verified through the stages of ground test, analysis and flight testing as it is difficult to predict.

During the flight test phase, the speed and / or altitude area of the aircraft should be gradually expanded to demonstrate aerodynamic stability and / or durability and to ensure that dangerous vibrations do not occur on lifting surfaces such as wings. For this purpose, a device capable of measuring the vibration of the aircraft wing must be provided. It is also necessary to analyze the vibration data acquired through these instruments to determine whether there is aero-hydroelasticity in the new armament or new assembly combination.

In particular, in the case of an airplane developed in-house, since it has all the design information for the aircraft, it is possible to appropriately modify the sensor and / or storage device necessary for the vibration measurement to be mounted inside the aircraft. However, in the case of an aircraft that has not been developed directly, it is not practically possible to retrofit the interior of the aircraft in order to mount the sensor or measuring equipment without sufficient design information. This is because it is not possible to determine the effects of modifications made to mount sensors or instrumentation on aircraft flight safety.

Due to the above data measurement problem, it is difficult to carry out the flight test to confirm the fitting between the aircraft and the new equipment even if the new aircraft such as the KF-16 is intended to be equipped with new armament or equipment.

1. Korean Patent Publication No. 10-2015-0012214 (Disclosure Date: February 03, 2015) 2. Korean Patent Publication No. 10-2004-0080117

1. Yoo, Hyun-Hyun et al., "A Study on Suppression of Vibration Loads in Low-Speed Rotating Rotors Using Harmonic Control (HHC) Technique" Korea Aerospace Research Institute (2013)

The present invention has been proposed in order to solve the problem according to the above background art, and it is an object of the present invention to develop a separate flight measurement instrument utilizing an armed mount outside the aircraft, without modifying the interior of the aircraft, The present invention provides an external mounting measuring instrument and a control method thereof, which enables a mounting conformity flight test to be performed.

In order to achieve the above-described object, the present invention develops a separate flight measurement device utilizing an armed mount outside the aircraft, without modifying the interior of the aircraft to mount the sensor or the measurement device, The present invention provides an external mounted measuring instrument capable of performing a measurement of a measurement result.

The external mounting measuring instrument may have a measuring instrument structure 110 structurally supporting a load to be mounted on a military aircraft.

Also, in the external mounting measurement instrument,

A measurement sensor 129 for measuring acceleration sensor data, stereo image data, flight information data, time data, and temperature sensor data of the military aircraft;

A data measuring device 121 for storing the acceleration sensor data, GPS data, time data, and temperature sensor data;

An image measuring device 123 for storing the image data; And

And a power signal distribution device 125 mounted on the armed mount of the military aircraft and converting the aircraft power supplied through the umbilical connector into direct current (DC) power.

At this time, the image measuring device 123 transmits the stereo image data photographed at different positions to the same remote point using the front high-speed camera 202 and the rear high-speed camera 204 from the RF signal distributor 201 And stores the time information together with the time information of the GPS data, and synchronizes the acceleration data and the stereo image data using the time information.

In order to improve the low-temperature operability, heat-generating pads 523-1 to 523-4 made of silicone rubber are attached to the storage disk provided in the front high-speed camera 202, the rear high-speed camera 204 and the image measuring device 123, Is mounted.

In addition, the external mounting measuring instrument supplies DC power to the power / signal distributing apparatus 125 in a state in which the power of the aircraft is not supplied, and supplies the DC power to the power signal distributing apparatus, the data measuring apparatus, And an end cap 210 connected to the ground inspection analysis equipment 130 so as to receive and control the stored data.

In addition, the front balance weight 212 and the rear balance weight 211 may be installed at regular intervals to adjust the center of gravity and the moment of inertia.

Also, a front three-axis acceleration sensor 206 and a rear three-axis acceleration sensor 209 may be installed in the measurement equipment structure 110 at predetermined intervals to obtain the acceleration sensor data.

The acceleration sensor data may be used to compensate the own vibration of the front high-speed camera and the rear high-speed camera.

In addition, altitude and speed information of the aircraft obtained using GPS data and information on the aircraft attitude obtained using the INS sensor are stored together so that the flight condition in the situation where the vibration data is acquired can be confirmed can do.

In addition, in a state in which the heating pad is mounted, the power of the heating pad is adjusted according to the internal temperature obtained through the temperature sensor.

In the absence of the military aircraft, the ground inspection analysis equipment 130 uses the aircraft power simulator 1250 to control the data measurement device 121, the power source signal distribution device 125, and the video measurement device 123 ) Is normally operated.

(A) a power supply signal distribution device 125 is mounted on the arming mount of the military aircraft, and the AC power of the aircraft supplied through the umbrella connector 521 is connected to the DC (Direct Current) power supply; (b) measuring the acceleration sensor data, the image data, the flight information data, the time data, and the temperature sensor data of the military aircraft by the measurement sensor 129; And (c) the data measuring device 121 stores the acceleration sensor data, the GPS data, the time data, and the temperature sensor data, and the video measuring device 123 stores the video data. The present invention can provide a control method of an on-board mounted measuring instrument.

In this case, the step (a) may include: determining whether the power source distribution apparatus is in an automatic mode or a manual mode; As a result of the determination, in the automatic mode, the flight information data, the temperature sensor data, the heating pad operation state data, and the internal power state data are stored in the storage module 620. In the manual mode, The method comprising the steps of:

At this time, the heating pad operation state may be such that the heating pad power is turned on when the internal temperature of the external mounting measurement instrument 120 is below a predetermined temperature, and the heating pad power is turned off when the internal temperature is higher than the predetermined temperature.

According to the present invention, the vibration of an aircraft can be measured without modifying the inside of the aircraft in order to mount the sensor and / or the measuring instrument.

As another effect of the present invention, the vibration data can be remotely measured using the stereo image information even in a region where the sensor is not mounted, and it is possible to measure vibrational data remotely by using the stereo image information, And the behavior characteristics can be confirmed.

In addition, another effect of the present invention is that the airplane is unnecessarily operated for power supply while downloading data after the flight, or the inconvenience of removing the equipment is improved.

1 is a schematic diagram of an apparatus for acquiring an external aircraft vibration data acquisition system according to an embodiment of the present invention.
2 is an external perspective view of the metrology equipment tube 111 shown in Fig.
3 is a perspective view of the rail structure 113 shown in FIG.
FIG. 4 is a configuration diagram of the on-board measurement equipment 120 shown in FIG.
5 is an overall configuration diagram of the external aircraft vibration data acquisition system shown in FIG.
6 is a functional block diagram of the power / signal distribution device 125 shown in FIG.
FIG. 7 is a flowchart showing the temperature control process of the power / signal distribution device 125 shown in FIG.
FIG. 8 is a flowchart illustrating the process of storing the on-board measurement equipment status information of the power / signal distribution device 125 shown in FIG.
9 is a functional block diagram of the data measuring apparatus 121 shown in FIG.
10 is a functional block diagram of the video measurement apparatus 123 shown in FIG.
11 is an example of acquiring remote vibration data using a stereo image according to an embodiment of the present invention.
FIG. 12 is an interface block diagram of the ground inspection analysis equipment 130 shown in FIG.

While the invention is susceptible to various modifications and alternative forms, specific embodiments thereof are shown by way of example in the drawings and will herein be described in detail. It is to be understood, however, that the invention is not to be limited to the specific embodiments, but includes all modifications, equivalents, and alternatives falling within the spirit and scope of the invention.

Like reference numerals are used for similar elements in describing each drawing.

The terms first, second, etc. may be used to describe various components, but the components should not be limited by the terms. The terms are used only for the purpose of distinguishing one component from another.

For example, without departing from the scope of the present invention, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component. The term "and / or" includes any combination of a plurality of related listed items or any of a plurality of related listed items.

Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs.

Terms such as those defined in commonly used dictionaries are to be interpreted as having a meaning consistent with the contextual meaning of the related art and are to be interpreted as either ideal or overly formal in the sense of the present application Should not.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings, in which like reference numerals refer to like elements throughout.

1 is a schematic diagram of an apparatus for acquiring an external aircraft vibration data acquisition system according to an embodiment of the present invention. Referring to FIG. 1, an external aircraft vibration data acquisition system 100 includes a measurement equipment structure 110 structurally supporting a load, a vibration and / or image information acquiring unit 110 installed in the measurement equipment structure 110 to acquire vibration and / And a ground inspection analysis device 130 that can download data from the ground to support analysis and check the equipment, and the like.

The measuring instrument structure 110 includes a measuring instrument tube 111 as an outer appearance, a rail structure 113 assembled with the layer equipment tube 111 and formed inside thereof, a balance weight 115 for balancing the balance, And a mobile storage box 117 capable of storing and moving the mobile storage box 117.

The on-board measuring apparatus 120 includes a data measuring apparatus 121 for obtaining a speed, an image measuring apparatus 123 for measuring a high-speed camera image, a power source signal distributing apparatus 125 for power / signal distribution, A measurement sensor 129 for measuring time, temperature, and the like, and a mounting cable 128 for connecting the devices and transmitting the power and data signals.

The ground inspection analysis device 130 controls the ground inspection device 131 and the video measurement device 123 for confirming whether or not the normal operation of each device, the power supply and the temperature information of each device, the front high speed camera 202 and the rear high speed camera A data analyzing unit 135 for controlling the image analyzing unit 133 and the data measuring unit 121 for checking and downloading the images photographed by the external measuring instrument 204, And an inspection cable 137 connected to the end cap 210 of the main body 120.

3 is a perspective view of the rail structure 113 shown in FIG. 1, and FIG. 4 is a perspective view of the on-board measurement equipment 120 shown in FIG. 3, Fig. 2 to 4, the measurement equipment structure 110 includes a measurement equipment tube 100, a rail structure 113, a nosecone 101, and balance weights 211 and 212.

The nose cone 101 is disposed in the shape of a spire at the front end of the measurement equipment structure 110 to perform functions of reducing air and / or wind resistance.

The balance weights 211 and 212 are constituted by a front balance weight 212 disposed at the front and a rear balance weight 211 disposed at the rear in order to balance the measurement equipment structure 110. In addition, the equipment for acquiring flight data is also considered to be new aircraft equipment from the point of view of the aircraft, so the suitability of the aircraft to the aircraft should be verified. To this end, the instrumentation structure 110 according to the present invention may have the same external shape and / or weight characteristics as ACMI (Air Combat Maneuvering Instrumentation) which is already certified to be mountable to a plurality of aircraft, So that no separate authentication is required.

However, since the equipment installed inside is different from ACMI, separate certification is required for electromagnetic compatibility (CE102, RE102) and environmental compatibility (temperature, altitude). These tests are also available on the ground using separate test facilities. Accordingly, the front and rear balance weights 212 and 211 are installed in front of and behind the measurement equipment structure 110 to have the same weight characteristics as the ACMI, so that the center of gravity and / or the moment of inertia of the equipment can be adjusted.

A GPS antenna 102 for receiving a GPS signal is disposed on the rear end side of the nose cone 101. An RF (Radio Frequency) signal distributor 201 for distributing an RF signal is disposed in front of the front balance weight 212, . Further, a front high-speed camera 202 for capturing a forward image, a power source signal distributor 125 for distributing power and / or signals, a rear high-speed camera 204 for shooting a rear image, a vertical vibration and twist of an aircraft wing A front three-axis acceleration sensor 206 for measuring directional vibration, a Global Positioning System (GPS) / INS (Inertia Navigation System) sensor 205 for acquiring flight information data, acceleration sensor data, GPS data, A data measuring device 121 for storing temperature sensor data, an image measuring device 123 for storing image data, a rear balance weight 211, a rear three-axis acceleration for measuring the vertical direction vibration and torsional direction vibration of the aircraft wing A sensor 209, and an end cap 210 for connection with the ground inspection analysis equipment 130, and the like.

5 is an overall configuration diagram of the external aircraft vibration data acquisition system shown in FIG. 5, a pylon 511 of the military aircraft 510 is configured to mount and connect the on-board measurement equipment 120 to the military aircraft 510, and a pylon 511 of the military aircraft 510 is connected to one side of the on- The umbrella connector 521 is constructed. The pylons 511 and the umbilical connector 521 are connected to an umbilical cable.

The navel connector 521 is connected to a power signal distributor 125 through an EMI (Electro Magnetic Interference) filter 521-1 to supply power suitable for each device in the apparatus. That is, the aircraft power is converted into DC (direct current) power and supplied.

The on-board measurement equipment 120 includes a data measurement unit 121 for acquiring data such as acceleration, an image measurement unit 123 for measuring a high-speed camera image, a power source signal distribution unit 125 for power / A measurement sensor (129 in Fig. 1), and the like. The GPS / INS module 205 is installed to acquire the flight information data together, and the GPS / INS data, which is the flight information data, is acquired from the power signal distribution device 125.

In particular, the measurement sensor 129 includes a GPS antenna 102, a GPS / INS module 205, two high-speed cameras 202 and 204, two three-axis acceleration sensors 206 and 209, and a temperature sensor 528. All data are time synchronized based on GPS time for time synchronization of acceleration, image, and / or GPS / INS data acquired on each device.

The two three-axis acceleration sensors 206 and 209 are mounted in three axial directions, respectively, in front and rear to measure vibration data in the aircraft wing. Thus, the vertical vibration and / or the torsional vibration of the aircraft wing can be measured.

In addition, as a useful method for remotely acquiring acceleration signals of other parts of the wing that are not attached with the acceleration sensor or of the external mounts of the other arming mounts, it is also possible to record the image of the desired site and extract the vibration data.

In addition, a low-temperature vulnerable storage device such as two high-speed cameras 202 and 204, a power source signal distributor 125 and a storage disk (for example, a solid state disk (SSD) 523-1 to 523-4) is applied to compensate for operability at low temperatures. The ground inspection analysis equipment 130 and each of the devices 125, 121, and 123 are interconnected using Ethernet communication in a 1: 1 ratio.

In addition, as the aircraft is operated at altitudes of tens of thousands of feet, the temperature can be drastically lowered according to flight altitude. To cope with this, the heating pad 523-1 to 523-4 is provided in a video equipment or the like which is vulnerable to low temperatures inside the equipment, and the power of the heating pad can be adjusted according to the internal temperature of the equipment using a temperature sensor.

The two high-speed cameras 202 and 204 are provided in the front and back to support image-based vibration data extraction. In addition, it has a feature of storing stereo image about a part where vibration data is to be obtained by using it.

However, since the camera mounting portion is also shaken, it is necessary to compensate the camera's own vibration in order to obtain accurate vibration data from the image. For this purpose, the above-described three-axis acceleration sensor data can be utilized. For accurate camera image correction, the vibration data and image data obtained from the acceleration sensor must be synchronized. For this, an embodiment of the present invention has a feature of using time information of GPS.

The altitude and / or speed information of the aircraft obtained using the GPS signal and the information on the aircraft attitude obtained using the GPS / INS module 205 are stored together so that the flight condition in the situation where the vibration data is acquired can be confirmed .

The ground inspection analysis equipment 130 is configured to interface with the on-site measurement equipment 120 through the end cap 210. Further, each of the devices 532 is connected through the interface panel 531. Each device 532 includes data analysis equipment, image analysis equipment, power signal distribution device inspection equipment, and aircraft power simulator.

The end cap 210 is capable of receiving data via Ethernet communication to eliminate the inconvenience of removing the on-board measurement equipment 120 from the aircraft 510 in order to receive the stored data.

Appropriate power must be supplied to receive data from the equipment. For this purpose, DC power can be supplied through the end cap 210 using the ground inspection analysis equipment 130 even when the aircraft power is not supplied. In addition, the same AC power as the aircraft can be supplied through the umbilical connector 521 in place of the aircraft, thereby confirming that the equipment is operating normally on the AC power source.

The data stored during the flight can be downloaded by using the ground inspection analysis equipment 130 and the operation of each device 125, 121, 123 and / or the inside temperature of the equipment, the operation of the heating pads 523-1 to 523-4 And so on.

6 is a functional block diagram of the power / signal distribution device 125 shown in FIG. Referring to FIG. 6, the power supply signal distributor 125 receives the AC power supplied through the umbilical connector through the EMI filter 521-1. The power supply signal control module 630 generates various output voltages through the power distribution module 640 composed of an alternating current / direct current (AC / DC) and a DC / DC converter from the AC power input from the aircraft 510 And supplies power to each device and / or sensor inside the on-board measuring equipment 120. [ The temperature control module 650 is provided with four temperature sensors installed in the power supply signal distribution 125 inside the onboard measurement equipment 120, the front high speed camera 202, the rear high speed camera 204 and the video measurement device 123 The transmitted signal is converted into digital temperature sensor data by using the ADC, and power of the heating pads 523-1 to 523-4 is controlled by using the temperature sensor data.

An Ethernet controller 610 for controlling an Ethernet signal, an internal temperature sensor 680 for sensing an internal temperature in the power supply signal distributor 125, and a storage module 620 for storing control, data, and the like are configured.

FIG. 7 is a flowchart showing the temperature control process of the power / signal distribution device 125 shown in FIG. Referring to FIG. 7, the temperature sensor data is collected and it is confirmed whether the state of the heating pad is on (steps S710 and S720).

If it is determined that the heating pad is on, it is determined whether the temperature is higher than about 20 占 폚 for 6 seconds (step S730).

In step S730, if the temperature is higher than about 20 deg. C for six seconds, the heating pad power is turned off, otherwise, the process goes to step S710 for collecting temperature sensor data.

On the other hand, if it is determined in step S720 that the heating pad is OFF, it is determined whether the temperature is lower than about 5 DEG C for 6 seconds (step S750).

In step S750, if the temperature is lower than about 5 占 폚 for six seconds, the heating pad power is turned on, otherwise, the process goes to step S710 for collecting the temperature sensor data.

That is, when the temperature of the heating pad falls below a predetermined temperature, the power of the heating pad is turned on, and when the temperature is again higher than a predetermined level, the heating pad is turned off.

FIG. 8 is a flowchart illustrating the process of storing the on-board measurement equipment status information of the power / signal distribution device 125 shown in FIG. Referring to FIG. 8, the power supply signal distribution device 125 has a function of collecting and / or storing data on flight information (GPS / INS) data, temperature sensor data, heat pad operating state, .

For this purpose, it supports Auto mode and Manual mode. Therefore, the data is collected and it is confirmed whether or not it is the auto mode (steps S810 and S820).

If it is determined in the automatic mode, the acquired data is stored in the storage module 620, which is a flash memory (step S830). Alternatively, if the mode is the manual mode, the user may transmit 10 Hz data to the user through the ground inspection analysis device 130 so that the 10 Hz data can be viewed in real time.

9 is a functional block diagram of the data measuring apparatus 121 shown in FIG. 9, the data measuring apparatus 121 includes a memory module 910 for storing measured data, an ADC module 920 for converting analog data into digital data, a GPS receiver module (not shown) for receiving GPS / INS data 930, an Ethernet controller 940 for controlling Ethernet communication, and the like. In addition, the forward and backward three-axis acceleration sensor data are converted into digital data through the ADC module 920 of the data measuring apparatus and then stored together with the GPS signal in the memory module 910.

10 is a functional block diagram of the video measurement apparatus 123 shown in FIG. 10, the video measurement device 123 includes an O / S (Operating System) storage device 1010, a CPU board 1020, a GPS board 1030, a front camera video storage device 1040, A storage device 1050, a heating pad 523-4, and the like. In addition, the image measuring device 123 uses a high-performance computer and a large-capacity image storage device to store images for 2 hours or more using a Giga Ethernet I / F (interface) for a high-speed camera image. It includes a GPS board, GPS receiver for time synchronization, and interfaces using RS-232 communication.

11 is an example of acquiring remote vibration data using a stereo image according to an embodiment of the present invention. Referring to FIG. 11, a reflection marker is attached to a position where the vibration data is to be acquired on the arm mounting base next to the mounting measurement apparatus, and two cameras are mounted on the front and rear of the mounting measurement apparatus during flight. The images of both cameras are synchronized with GPS time. Then, a separate program is used to extract position information and displacement and acceleration information on which the reflection marker is attached.

12 is an interface configuration block diagram of the ground inspection analysis equipment 130 shown in FIG. 12, the ground inspection analysis equipment 130 includes an interface panel 531, a data analysis equipment 1210 for analyzing measurement data, an analysis equipment 1220 for analyzing image data, and a power supply signal distribution device (1240), a power supply simulator (1250) that simulates a power supply distribution device inspection device (1230), a 220V AC commercial power supply (1240) used as a main power source for ground inspection analysis equipment, and a 115V AC aircraft power supply do.

The ground inspection analysis equipment 130 can be connected to the power signal distribution device 125, the data measurement device 121 and the video measurement device 123 through the end cap 210 to perform the inspection. DC power is supplied together via the end cap 210. [ In addition, when the on-board measuring instrument is mounted on an aircraft and operated, AC power is supplied from the aircraft through the umbrella connector 521, so that in order to simulate the environment mounted on the aircraft even in the absence of an aircraft, A power simulator 1250 may be used to generate 115 V, 300 Hz AC power, which is the same as the power supplied by the aircraft, and to supply power to the umbrella connector 521.

100: External Aircraft Vibration Data Acquisition System
110: Measuring equipment structure 120: Onboard measuring equipment
130: Ground inspection analysis equipment
111: Measuring equipment tube 101: NOZCON
102: GPS (Global Positioning System) antenna
121: Data measuring device
123: Image measuring device 125: Power supply signal distributing device
113: Rail structure 201: RF signal distributor
202: forward high speed camera 204: rear high speed camera
205: GPS / INS (Global Positioning System / Inertia Navigation System) module
206: front three-axis acceleration sensor 209: rear three-axis acceleration sensor
210: end cap 211 rear balance chu
212 Front Balance Chu

Claims (13)

1. An on-board metrology instrument having a metrology equipment structure (110) structurally supporting a load to be mounted on a military aircraft,
A measurement sensor 129 for measuring acceleration sensor data, stereo image data, flight information data, time data, and temperature sensor data of the military aircraft;
A data measuring device 121 for storing the acceleration sensor data, GPS data, time data, and temperature sensor data;
An image measuring device 123 for storing the image data; And
And a power signal distribution device (125) mounted on the armed mount of the military aircraft to convert the aircraft power supplied through the umbrella connector into direct current (DC) power,
The image measuring apparatus 123 transmits stereo image data obtained by photographing the same remote point at different positions to the GPS signal branched from the RF signal distributor 201 by using the forward high speed camera 202 and the rear high speed camera 204, And synchronizes the acceleration data with the stereo image data using the time information.
delete The method according to claim 1,
Characterized in that a heating pad made of silicone rubber is mounted on a storage disk provided in a front high-speed camera (202), a rear high-speed camera (204) and an image measuring device (123) .
The method according to claim 1,
The DC power is supplied to the power / signal distribution device 125 in a state where the power of the aircraft is not supplied, and the data stored in the power signal distribution device, the data measurement device, and the image measurement device can be downloaded and controlled by Ethernet communication And an end cap (210) connecting the ground inspection analysis equipment (130) to the ground inspection analysis equipment (130).
The method according to claim 1,
And a front balance weight (212) and a rear balance weight (211) are installed at regular intervals to adjust the center of gravity and moment of inertia. delete The method according to claim 1,
Wherein the acceleration sensor data is used to compensate the self-vibrations of the forward high-speed camera and the rear high-speed camera.
The method according to claim 1,
The altitude and speed information of the military aircraft obtained by using GPS (Global Positioning System) data and the aircraft posture obtained by using the INS (Inertia Navigation System) sensor so that the flight condition in the situation where the vibration data is acquired can be confirmed And the information is stored together.
The method of claim 3,
Wherein power of the heating pad is adjusted according to an internal temperature obtained through a temperature sensor in a state where the heating pad is mounted.
5. The method of claim 4,
The ground inspection analysis apparatus 130 may be connected to the data measurement apparatus 121 and the power signal distribution apparatus 125 by using the aircraft power simulator 1250 to supply the same power as the aircraft even in the absence of the military aircraft. , And the video measuring apparatus (123) are normally operated.
A method of controlling an on-board measurement instrument having a metrology equipment structure (110) structurally supporting a load to be mounted on a military aircraft,
(a) a power source signal distributor 125 is mounted on the armed mount of the military aircraft, converting the aircraft power supplied through the umbilical connector into a direct current (DC) power, and providing the same;
(b) measuring the acceleration sensor data, the stereo image data, the flight information data, the time data, and the temperature sensor data of the military aircraft by the measurement sensor 129; And
(c) storing the acceleration sensor data, flight information data, time data, and temperature sensor data by the data measuring apparatus 121 and storing the image data by the image measuring apparatus 123,
The step (a) may include: determining whether the power source distribution apparatus is in an automatic mode or a manual mode;
As a result of the determination, in the automatic mode, the flight information data, the temperature sensor data, the heating pad operation state data, and the internal power state data are stored in the storage module 620. In the manual mode, The method comprising the steps of; delete 12. The method of claim 11,
The heating pad operation state is such that if the internal temperature of the external mounting measurement instrument 120 is below a certain temperature, the heating pad power is turned on, and if the internal temperature is above the predetermined temperature, the heating pad power is turned off .

Images