KR101354976B1 - Aerial radiological survey system - Google Patents

Abstract

The present invention relates to a radiological survey system utilizing an aircraft, comprising; a frame for mounting a radiation measuring instrument installed in an outside lower part of a rotary-wing aircraft (1); a mounting structure (2) for the radiation measuring instrument, secured in an upper part of the frame (7) for mounting the radiation measuring instrument; a cable (8) for transmitting and receiving data of the radiation measuring instrument connected to the mounting structure (2) for the radiation measuring instrument; an external cable line (9) for power supply connection; a survey path checking system (4) installed on a rear face of an inside driver seat of the rotary-wing aircraft(1); a portable computer (5) having a built-in data collection and analysis program (6) and installed in an upper part of the survey path checking system (4); and a position checking system (3) installed on a rear face of the portable computer (5). [Reference numerals] (4) Survey path checking system; (5,6) Display (computer) + program

Description

Radioactive survey system using aircraft {Aerial radiological survey system}

The present invention relates to a radioactive contamination detection measurement system using an aircraft for the purpose of minimizing the radiation exposure of the people through rapid exploration and emergency response in the event of a radioactive accident.

The present invention has not been developed so far in Korea as a system using an aircraft to perform a quick exploration when a radioactive accident occurs in a site dealing with a nuclear power plant or a general radioactive material. Routine fixed or mobile radiation surveys are conducted to assess the impact on the environment during normal operation of a nuclear power plant. However, these methods are not appropriate for the following reasons when actual radioactive material leaks:

    1. Only accessible areas can measure data.

    2. May result in unnecessary radiation exposure of exploration personnel.

    3. It takes time for emergency measures to be taken.

    4. High manpower is required for exploration of extensive contaminated areas.

In addition, in recent years, the use of radioisotopes is frequently lost or stolen, and these materials are illegally traded or lost, becoming invincible sources and causing unexpected exposure to humans. Such radioactive aerial exploration techniques can also be used effectively for the rapid exploration of lost, stolen and relocated radioactive material over a wide area.

In Korea, for example, Korean Patent Registration No. 1009673640000 Airborne airborne and radioactive oxo trapping device for aircraft installation In the invention, a device for collecting and analyzing particulate radionuclides in the air in real time to the external rocket launcher A suction nozzle (1) mounted at an inlet to collect air suspended particles introduced through a nozzle during a flight, and a filter holder (2) installed at a rear surface of the suction nozzle (1) to support a filter paper (2-1). ), A metal mesh (3) supporting the filter paper (2-1), an air filter (4) installed on the rear of the metal mesh (3), a hepa filter (installed on the rear of the air filter (4) ( 5), the activated carbon filter 6 installed on the rear of the HEPA filter 5, the suction flow rate measuring unit 7 installed on the rear surface of the activated carbon filter 6, and the rear side of the suction flow rate measuring unit 7 Airborne atmospheric and radioactive airborne aircraft consisting of installed air outlets (8) Oxo trapping device is open,

In the case of the invention, the WCDMA or CDMA and GM radiation dosimeter, GPS function, RF wireless local area communication method, etc., tracks the location of the radiation source to be used while moving in real time. Remotely communicating with the RFRP 200 by the RF module 50 of the main body to measure and manage the peripheral radiation dose of the radiation source using a remote remote transmission or image transmission and reception device, and a dose rate around the mobile radiation source 210. Monitoring the light using the GM monitor 40, transmitting and receiving the GPS satellite 400 by the GPS receiver 10 to determine the position of the mobile radiation source 210, and the RF module 50 of the main body. Data received from the GPS receiver 10, data about the position of the mobile radiation source 210 by the GPS receiver 10, and lines around the mobile radiation source 210 using the GM monitor 40. The rate monitoring data is analyzed by the ultra low power microprocessor 60, and the analysis result is remotely connected to the central control center 300 by the CDMA 20 or the WCDMA 21 at the request of the central control center 300. Communicating, and displaying and monitoring the status and communication status of the main body 1 including the dose rate by the LCD display 30, and monitoring using the GM monitor 40 includes two rings. The buffer is monitored using a dose rate measurement algorithm that automatically calculates the real-time dose rate according to the amount of the count rate, and the analysis results are sent to the CDMA 20 or the WCDMA 21 at the request of the central control center 300. In the step of remote communication with the central control center 300 by the CDMA 20 used for remote communication with the central control center 300 sends a command to the mobile radiation source remote control device in the SMS (SMS) method, CDMA (20) What modems have It transmits the data collected through the TCP / IP connection to the central control center 300, and directly monitors the user's surroundings of the mobile radiation source 210 through the image using a WCDMA 21 modem for remote communication Remote monitoring method of mobile radiation source is disclosed,

 A suction nozzle 1 installed at an inlet in Korean Patent Publication No. 1009673640000 (20100624), a filter paper holder 2 installed at a rear surface of the suction nozzle 1 to support a filter paper 2-1, A metal mesh (3) supporting the filter paper (2-1), an air filter (4) installed at the rear of the metal mesh (3), a hepa filter (5) installed at the rear of the air filter (4), Activated charcoal filter (6) installed on the rear of the hepa filter (5), suction flow rate measurement unit (7) installed on the rear of the activated carbon filter (6), air outlet installed on the rear of the suction flow rate measurement unit (7) (8) airborne atmospheric dust collection and radioactive oxo collection device is disclosed,

In foreign countries, radio equipment, multi-channel analyzers, location information systems, and communication equipment using modems are mainly installed inside helicopters or fixed-wing aircraft to measure radiation levels. In Canada's Exploranium, the radiometer is designed to be easy to open and close, which is sealed by an external housing to make it easy to mount the measurement sensor inside.

1. Domestic registered patent publication No. 1009673640000 2. National Registered Patent Publication No. 1009605380000 3. Korean Registered Patent Publication No. 1009673640000 (20100624)

The above techniques are as follows. First, atmospheric dust and radioactive oxo capture devices bring radioactive materials captured by aircraft to the ground and conduct radionuclide analysis to detect radioactive accidents in the domestic or neighboring countries rather than measuring actual radiation dose. Secondly, the method of remote monitoring of mobile radioactive sources is based on the real-time monitoring of the radioactive devices generated by radioisotopes used by non-destructive companies in order to prevent accidents caused by the loss of radioisotopes. As it has a function to track according to movement, it is different from the actual radiation level exploration. Third, foreign countries have developed a system to measure the radiation level by using a helicopter or a fixed-wing aircraft. Mainly used, mounted inside the helicopter By mounting to the aircraft external to eliminate the shielding effect of the helicopter body for generating improve the efficiency of the radiation and measuring the time,

In addition, it is equipped with a sensor that maintains a constant temperature to alleviate internal temperature changes and internal shocks caused by mounting outside of the aircraft, and reinforces the cushioning material to prevent the fluctuation of the radiometer and prevents sudden changes in temperature. It is a problem to be solved by the present invention to prevent a decrease in radiometric efficiency due to phosphorus flight.

In order to solve the above problems, the present invention provides a radiometer mounting frame (7) installed at an outer lower portion of a rotorcraft aircraft (1), and a radiometer mounting structure (2) placed on an upper portion of the radiometer mounting frame (7). ), A cable 8 for transmitting and receiving data of the radiation measuring instrument connected to the radiation measuring instrument mounting structure 2 and an external cable line 9 for power connection, and an exploration path installed at the rear of the inner driver's seat of the rotorcraft 1. Confirmation system (4), a portable computer (5) installed on the upper part of the exploration path confirmation system (4) and a data collection and analysis program (6) therein, and a position check installed on the rear of the portable computer (5). It is a problem solving means of the present invention to provide a radioactive exploration system utilizing an aircraft composed of a system (3).

The present invention is an area inaccessible to humans or vehicles to find out the location of a large amount of radioactive material due to a serious accident at a nuclear power plant or when the high level radioactive material used in a general site is stolen or lost. As a means of rapid radiological exploration in a wide range of contaminated areas, however, aircraft can be used to effectively reduce the radiation exposure of exploration personnel and to make decisions for the rapid evacuation of people due to radiological accidents.

In fact, during the 2011 Fukushima nuclear accident, the United States National Nuclear Security Commission (NNSA) quickly assessed the radioactive leaks in the northeastern part of Japan using aircraft to create a map of radiation pollution and to find out the direction of the radioactive cloud. It was used for the rapid evacuation of residents, and in 1987 in Goiania, Brazil, it was effectively used for exploration of radioactive contamination in a wide range of areas, even in the event of an accident caused by radioactive materials used in medical irradiation equipment. Has contributed to

Figure 1 Overall view of the radioactive exploration system using the aircraft
2 is a diagram showing the internal structure of the radiation measuring instrument mounting structure 1
3 and 4 the internal configuration of the radiation measuring instrument mounting structure 2
5 is a diagram showing the internal structure of the radiation measuring instrument mounting structure 3
6 and 7 cover configuration of the radiation measuring instrument mounting structure
Figure 8 Another example of a radiometer mounting structure

The present invention provides a radiometer mounting frame (7) installed on the outer lower portion of the rotorcraft (1), a radiometer mounting structure (2) placed on top of the radiometer mounting frame (7), and the radiometer mounting structure ( 2) the cable 8 for data transmission and reception of the radiometer connected to the radiometer and the external cable line 9 for power connection, the exploration path checking system 4 installed at the rear of the inner flight seat of the rotorcraft 1, and the Aircraft comprising a portable computer (5) installed on the top of the exploration path confirmation system (4) and a data collection and analysis program (6), and a positioning system (3) installed on the rear of the portable computer (5). It relates to a radioactive exploration system utilizing the

The present invention improves the efficiency of radiation measurement by mounting on the outside of the aircraft in order to eliminate the shielding effect caused by the base of the helicopter when mounted on the inside of the aircraft by using the helicopter outside, the instrument caused by mounting outside the aircraft It is equipped with a sensor that keeps the temperature constant to alleviate internal temperature changes and internal shocks caused by flying, and reinforces the buffer material to prevent the shaking of the radiometer.This prevents sudden changes in temperature and reduces radiation measurement efficiency due to irregular flight. Reduced.

The measured data is transmitted to the central server via radio transmitter and receiver along with the identification of radionuclide through GPS and the location data through GPS.

The present invention provides a radiation measuring instrument structure mounting frame (7) that firmly secures the structure (2) equipped with a radiometer inside both sides of the lower landing support of the rotorcraft (1) to transmit and receive data of the radiometer The cable (8) and the external battery cable (9) for power connection are pulled into the helicopter through the connection passage at the bottom of the helicopter and connected to the equipment for data collection, and the GPS receiver (3) inside the helicopter. The survey route identification system (4) and the portable computer (5) and the counting rate for each channel to analyze the data collected from the radiometer. It consists of a program 6 for analyzing the nuclide spectrum.

2 is an internal configuration of the radiometer mounting structure 2,

Structure inside the NaI-Scintillator instrument (4 "× 4" × 16 ") (12) that enters up to four external to reduce the weight by using a relatively light material for the protection of aluminum (10), the sensor bracket (11 for fixing ), The instrument to withstand the external shock, and the connector 15 for transmitting the collected measurement data to the outside can transmit data from the four instruments at the same time, the external power supply for the instrument and temperature control Connector (13) for connection with the controller and the control device for controlling the internal temperature and the screen (16) and the bracket (17) for mounting on the helicopter, the handle (19) for mounting on the helicopter or moving the structure And the lower portion 18 of the structure.

Referring to Figures 3 and 4 illustrating the internal configuration of the impact and temperature control of the radiation measuring instrument mounting structure (2) as follows.

The wire 21 and the support 22 for mitigating the external impact of the measuring sensor 12 are mounted at the bottom four corners of the inner sensor fixing bracket 11 to withstand the force of 5G. At the bottom of the bracket 11, a heater 23 for temperature control and a sensor 16 for temperature control are attached so that the internal temperature is maintained at 0 ° C or higher.

Referring to Figure 5, the configuration of the radiometer mounting structure 2 cover is as follows.

The radiometer mounting structure uses a cover 24 to facilitate the mounting of the instrument and secures the cover tightly by installing a clamp 26 for the locking device, and the O-ring inside the cover to block rain or moisture from the outside. Closed with 25.

Hereinafter, the present invention will be described in detail with reference to the drawings.

2, internal structure of the radiation measuring instrument mounting structure 1, 3 and 4 internal structure of the radiation measuring instrument mounting structure 2, 5 internal configuration of the radiation measuring instrument mounting structure 3, 6 and 7 cover of the radiation measuring instrument mounting structure 8, a rotorcraft aircraft 1, a radiation instrument mounting structure 2, a positioning system 3, an exploration path checking system 4, and a portable computer 5 are shown. ), Data collection and analysis program (6), radiation measuring instrument mounting frame (7), cable for transmitting and receiving data of radiation measuring instrument (8), external battery wire (9) for power connection, structure equipped with radiometer (10) ), Mounting bracket (11), NaI- flash meter sensor (12), connector for power connection (13), power battery (14), connector for data transmission (15), temperature control sensor and display screen 16, helicopter mounting bracket (17), the lower frame of the structure 18, the handle 19 for the movement of the structure, the measuring sensor internal support frame 20, the wire 21 for the instrument shock alleviation, the wire support 22, for temperature control It can be seen that the heater 23, the cover 24, the O-ring 25 inside the cover for waterproofing, and the cover fixing clamp 26 are shown.

Referring to the structure, the radioactive exploration system utilizing the aircraft of the present invention, as shown in Figure 1,

A radiometer mounting frame 7 provided on the outer lower portion of the rotorcraft 1, a radiometer mounting structure 2 placed on an upper portion of the radiometer mounting frame 7, and the radiometer mounting structure 2; A cable for data transmission and reception of the connected radiometer (8) and an external cable line (9) for power connection,

An exploration path confirmation system 4 installed on the inside of the inner flight seat of the rotary wing aircraft 1, and a portable computer 5 installed above the exploration path confirmation system 4 and having a data collection and analysis program 6 embedded therein. ), And the positioning system (3) installed on the rear of the portable computer (5),

The radiometer mounting structure 2 is shown in Figures 2 to 7,

It is composed of a body 10, a lower frame 18 of the structure installed on the lower portion of the body 10, and a cover 24 located on the upper portion of the body 10,

The body 10 has a connector 13 for connecting power to the front center, a power battery 14 connected to the connector 13, and a data transmission installed at one side of the connector 13 for connecting the power. Connector 15,

It consists of a temperature control sensor and a display screen 16 installed on one side of the connector 15 for data transmission, and a handle 19 for the movement of the structure of the four installed in the front and rear surfaces on both lower sides,

The lower frame 18 is two helicopter mounting brackets 17 which are spaced apart at regular intervals on both sides of the front surface, and are installed on the inner upper portion of the lower frame 18 and are located on the upper side of the four wire supports 22. Consists of a fixed instrument by the wire 21 for shock mitigation,

The measuring device has a structure in which four NaI- flash meter sensors 12 installed on the front surface and four measuring sensor fixing brackets 11 mounted on the rear surface of the NaI- flash meter sensor 12 are configured in parallel.

6 and 7, the cover 24 includes an O-ring 25 inside the cover for waterproofing and a plurality of cover fixing clamps 26 spaced apart from each other at regular intervals. It can be seen that the structure is configured.

Referring to the assembly and use state, first, as shown in Figure 5, the measuring instrument fixing bracket 11 installed on the back of the NaI- scintillation measuring instrument sensor 12, the instrument at the bottom of the four places near the corner of the instrument in which four integrated in parallel After placing the two wire support (22) provided with a wire 21 for shock mitigation,

3 and 4, installed on the upper portion of the lower structure frame 18, the body 10 is placed on the edge of the lower frame frame 18, the cover 24 of FIG. Position and fix the plurality of cover fixing clamps 26 installed at regular intervals on the

Connect the connector 13 and the power battery 14 for the power connection to the front center portion installed in the front of the body 10, the data transmission cable (8) of the radiometer to the connector 15 for the installed data transmission After connecting

Using the handle 19 for the movement of the structure installed on both sides of the body 10,

Fixed to the upper part of the radiation measuring instrument mounting frame (7) installed on the outer lower portion of the rotorcraft (1), the exploration path confirmation system (4) for the data transmission and reception cable (8) and the external cable line (9) for power connection And then assembled to the portable computer 5 and the positioning system 3, respectively,

When the aircraft 1 flies, the airborne pollution level is measured by the NaI- scintillation sensor 12 and the portable computer 5 and the probe through the data transmission / reception cable 8 of the radiometer. Once sent to the route identification system (4), the radionuclide identification and positioning system (3) is passed through a data collection and analysis program (6) to the central server via a radio transmitter and receiver along with the position data via GPS. The radiation map will be used and used for emergency measures.

Rotorcraft aircraft (1), radiometer mounting structures (2), positioning systems (3)
Exploration path verification system (4), portable computer (5), data acquisition and analysis program (6), radiographic instrument structure mounting frame (7), radiographic data transmission / reception cable (8), external battery cable for power connection (9), body (10), mounting bracket for measuring sensor (11), NaI- flash meter sensor (12), connector for power connection (13), power battery (14), connector for data transmission (15) , Temperature control sensor and display screen (16), helicopter mounting bracket (17), structure lower frame (18), handle for moving the structure (19), measurement sensor internal support frame (20), Wire 21, wire support 22, heater 23 for temperature control, cover 24, O-ring 25 inside cover, cover fixing clamp 26,

Claims (5)

delete delete In radioactive exploration system using aircraft,
A radiometer mounting frame 7 provided on the outer lower portion of the rotorcraft 1, a radiometer mounting structure 2 placed on an upper portion of the radiometer mounting frame 7, and the radiometer mounting structure 2; A cable for data transmission and reception of the connected radiometer (8) and an external cable line (9) for power connection,
An exploration path confirmation system 4 installed on the rear of the inner driver's seat of the rotary wing aircraft 1 and a portable computer 5 installed above the exploration path confirmation system 4 and having a data collection and analysis program 6 therein. And, consisting of a positioning system (3) installed on the rear of the portable computer (5),

The radiation measuring instrument mounting structure (2) is composed of a body 10, a structure lower frame 18 is installed on the lower portion of the body 10, and a cover 24 located on the upper portion of the body (10) ,
The body 10 has a connector 13 for connecting power to the front center, a power battery 14 connected to the connector 13, and a data transmission installed at one side of the connector 13 for connecting the power. Connector 15,
It consists of a temperature control sensor and a display screen 16 installed on one side of the connector 15 for data transmission, and a handle 19 for the movement of the structure of the four installed in both front and rear on both sides lower,

The lower frame 18 is two helicopter mounting brackets 17 which are spaced apart at regular intervals on both sides of the front surface, and are installed on the inner upper portion of the lower frame 18 and are located on the upper side of the four wire supports 22. Radioactive exploration system using an aircraft, characterized in that it comprises a measuring instrument fixed by a wire (21) for shock mitigation.
delete 4. The structure of claim 3, wherein the measuring device has a structure in which four NaI- flash meter sensors 12 installed on the front surface and four measuring sensor fixing brackets 11 mounted on the rear surface of the NaI- flash meter sensor 12 are configured in parallel. A radioactive exploration system utilizing an aircraft.

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