WO2015051665A1 - 对飞机进行检查的系统和方法 - Google Patents

对飞机进行检查的系统和方法 Download PDF

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Publication number
WO2015051665A1
WO2015051665A1 PCT/CN2014/083366 CN2014083366W WO2015051665A1 WO 2015051665 A1 WO2015051665 A1 WO 2015051665A1 CN 2014083366 W CN2014083366 W CN 2014083366W WO 2015051665 A1 WO2015051665 A1 WO 2015051665A1
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WO
WIPO (PCT)
Prior art keywords
detector
ray
aircraft
inspected
ray source
Prior art date
Application number
PCT/CN2014/083366
Other languages
English (en)
French (fr)
Inventor
康克军
李荐民
顾菁宇
李元景
李玉兰
刘耀红
谭桢
吴玉成
王伟珍
Original Assignee
清华大学
同方威视技术股份有限公司
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 清华大学, 同方威视技术股份有限公司 filed Critical 清华大学
Priority to PL14786438T priority Critical patent/PL2884269T3/pl
Priority to EP14786438.3A priority patent/EP2884269B1/en
Priority to US14/399,566 priority patent/US10088595B2/en
Publication of WO2015051665A1 publication Critical patent/WO2015051665A1/zh

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N23/00—Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups G01N3/00 – G01N17/00, G01N21/00 or G01N22/00
    • G01N23/02—Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups G01N3/00 – G01N17/00, G01N21/00 or G01N22/00 by transmitting the radiation through the material
    • G01N23/04—Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups G01N3/00 – G01N17/00, G01N21/00 or G01N22/00 by transmitting the radiation through the material and forming images of the material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
    • G01V5/00—Prospecting or detecting by the use of ionising radiation, e.g. of natural or induced radioactivity
    • G01V5/20—Detecting prohibited goods, e.g. weapons, explosives, hazardous substances, contraband or smuggled objects
    • G01V5/22—Active interrogation, i.e. by irradiating objects or goods using external radiation sources, e.g. using gamma rays or cosmic rays
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01V—GEOPHYSICS; GRAVITATIONAL MEASUREMENTS; DETECTING MASSES OR OBJECTS; TAGS
    • G01V5/00—Prospecting or detecting by the use of ionising radiation, e.g. of natural or induced radioactivity
    • G01V5/20—Detecting prohibited goods, e.g. weapons, explosives, hazardous substances, contraband or smuggled objects
    • G01V5/22—Active interrogation, i.e. by irradiating objects or goods using external radiation sources, e.g. using gamma rays or cosmic rays
    • G01V5/232—Active interrogation, i.e. by irradiating objects or goods using external radiation sources, e.g. using gamma rays or cosmic rays having relative motion between the source, detector and object other than by conveyor
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01L—SEMICONDUCTOR DEVICES NOT COVERED BY CLASS H10
    • H01L27/00—Devices consisting of a plurality of semiconductor or other solid-state components formed in or on a common substrate
    • H01L27/14—Devices consisting of a plurality of semiconductor or other solid-state components formed in or on a common substrate including semiconductor components sensitive to infrared radiation, light, electromagnetic radiation of shorter wavelength or corpuscular radiation and specially adapted either for the conversion of the energy of such radiation into electrical energy or for the control of electrical energy by such radiation
    • H01L27/144—Devices controlled by radiation
    • H01L27/146—Imager structures
    • H01L27/14601—Structural or functional details thereof
    • H01L27/14618—Containers
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N2223/00—Investigating materials by wave or particle radiation
    • G01N2223/60—Specific applications or type of materials
    • G01N2223/631—Specific applications or type of materials large structures, walls
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01J—ELECTRIC DISCHARGE TUBES OR DISCHARGE LAMPS
    • H01J37/00—Discharge tubes with provision for introducing objects or material to be exposed to the discharge, e.g. for the purpose of examination or processing thereof
    • H01J37/02—Details
    • H01J37/023—Means for mechanically adjusting components not otherwise provided for

Definitions

  • Embodiments of the present invention relate to a radiation safety inspection system that uses an aircraft as an object to be inspected. Background technique
  • backscattering based scanning system can be used for aircraft scanning.
  • the principle of backscattering is to place the radiation source and the detector on the same side of the object to be tested.
  • the X/Gamma particles emitted by the radiation source are incident on the object to be inspected, and some of the particles are absorbed by the object to be inspected;
  • the sample is scattered.
  • the scattering angle is less than 90 degrees, the scattered photons penetrate the object.
  • the scattering angle is greater than 90 degrees, the scattered photons are bounced off from the incident side.
  • Backscattering technology is to place the source and detector on the same side of the object to detect backscattered photons with a scattering angle greater than 90 degrees.
  • the backscatter product has a small footprint and flexible use.
  • this type of scanning system is not designed specifically for aircraft inspection and has some limitations in its application to aircraft scanning.
  • the backscatter scanning system has low ray energy and insufficient penetrating power to penetrate the wing and fuselage for complete and thorough inspection.
  • the ray and the low-Z substance are scattered at a large angle, and many particles are bounced back and cannot penetrate deep into the object to be inspected.
  • backscatter products are typically based on a mobile vehicle platform and do not provide a comprehensive inspection of all parts of the aircraft, such as higher ground (tail) or lower (bottom of the business aircraft).
  • the vehicle-based backscatter type detection system needs to move the equipment along the fuselage and the wings on both sides when used for aircraft scanning, and the scanning efficiency is low. Summary of the invention
  • an aircraft inspection system comprising: a gantry; a ray source for emitting a beam of radiation, the source of radiation being located on the gantry and movable on the gantry; For receiving a beam of radiation and converting it into an output signal, the detector being disposed in a trench coplanar with the beam of the source; a controller coupled to the detector and the source, the control station.
  • the radiation source emits a beam of rays as the aircraft being inspected moves through the scanning area formed by the radiation source and the detector, and controls the detector to receive a beam of rays from the source that penetrates the inspected aircraft;
  • Image generation module used An output signal of the detector is received to generate a top view transmission image of the aircraft under inspection.
  • the gantry has a sliding guide that allows the ray source to move along the sliding guide, and the detector is slidable along the guide rail in the trench in synchronization with the ray source; the controller controls the The radiation source is moved to a predetermined position along the slide rail, and the detector is controlled to synchronously move to the side to a position corresponding to the predetermined position, thereby performing a transmission inspection on the side of the aircraft to be inspected.
  • the length of the detector is less than or equal to one-half of the width of the gantry.
  • the source of radiation is specifically an accelerator or a source of radiation that produces X-rays or Gamma rays.
  • the detector specifically comprises an X-ray or Gamma ray sensitive gas or solids detector.
  • the detector is fixed in the trench.
  • the gantry has a sliding rail that allows the ray source to move along the sliding rail; the controller controls the ray source to move to one side along the sliding rail, thereby as described for the inspected aircraft The side is examined for transmission.
  • the length of the detector is greater than or equal to two-thirds of the width of the gantry.
  • the ray source emits a first ray beam of a first energy and a second ray beam of a second energy
  • the detector receives a first ray beam and a second ray beam
  • the image generation module receives the detection
  • the output signal of the device thus generates a dual energy transmission image of the aircraft being inspected.
  • said detector includes a first detection array responsive to a first portion of a beam of radiation and a second detection array disposed below said first detector array and responsive to said second portion of said beam of radiation,
  • the image generation module receives output signals of the first detection array and the second detection array to generate a dual energy transmission image of the aircraft under inspection.
  • the radiation source emits a first angle beam and a second angle beam
  • the detector comprises a first angle detection array disposed in the respective trench at a predetermined interval substantially parallel to the gantry and a second angle detecting array, respectively receiving a first angle beam and a second angle beam that penetrate the inspected aircraft, the image generation module receiving an output signal of the first angle detection array and the second angle detection array to generate A double-angle transmission image of the aircraft being inspected.
  • the height of the gantry is adjustable.
  • an aircraft inspection method comprising: from being disposed on a gantry The radiation source emits a beam of radiation on the gantry and movable on the gantry; receiving a beam of radiation and converting it by a detector disposed in a trench coplanar with the beam of radiation of the source Outputting a signal; controlling the radiation source to emit a beam of rays when the inspected aircraft moves through the scanning area formed by the radiation source and the detector, and controlling the detector to receive the penetration of the radiation source
  • the beam of the aircraft is examined; an output signal of the detector is received to generate a top view transmission image of the aircraft being inspected.
  • the method further comprises the steps of: controlling the radiation source to move to one side along the sliding rail to a predetermined position, and controlling the detector to synchronously move to the side to a position corresponding to the predetermined position, thereby A transmission inspection is performed on the side of the aircraft under inspection.
  • a system for inspecting an aircraft comprising: a gantry; at least two ray sources emitting a beam of rays, and the at least two sources of radiation are located on the gantry and they The emitted beam is coplanar; a detector for receiving the beam of radiation and converting it into an output signal, the detector being disposed in a trench coplanar with the beam of the source; a controller, and the detecting And the at least two radiation sources are connected to control the at least two radiation sources to emit a beam of rays when the inspected aircraft passes through the scanning area formed by the at least two radiation sources and the detector, and control the detector Receiving a beam of rays from the at least two sources that penetrate the inspected aircraft; and an image generation module for receiving an output signal of the detector to generate a top view transmission image of the inspected aircraft.
  • FIG. 1 is a schematic structural view of a system for inspecting an aircraft according to an embodiment of the present invention
  • FIG. 2 is a block diagram showing the structure of a system for performing a security check on an aircraft according to another embodiment of the present invention
  • Figure 3 is a block diagram showing the structure of a system for performing a security check on an aircraft according to still another embodiment of the present invention.
  • FIG. 4 is a block diagram showing the structure of a system for performing a security check on an aircraft according to still another embodiment of the present invention.
  • FIG. 5 shows a structural diagram of a system for performing a security check on an aircraft according to other embodiments of the present invention. Intention.
  • the radiation source and the detector are respectively located above and below the aircraft fuselage, the radiation source generates X/Gamma rays, penetrates the aircraft under test, and the detector array receives X/Gamma rays into an output signal.
  • the top view transmission image is produced in real time.
  • FIG. 1 shows a schematic structural view of a system for inspecting an aircraft in accordance with one embodiment of the present invention.
  • the system shown in Fig. 1 includes a radiation source 115, a gantry 121, a detector 118, a controller 112, and an image generation module 111.
  • a source 115 such as an X-ray source or a Gamma source, emits a beam of radiation.
  • the gantry 121 carries a radiation source 115 such that the radiation source 115 emits an X-ray beam downward.
  • Detector 115 is disposed in a trench that is coplanar with the beam of radiation from the source, such as in the trench of ground 110 as shown in FIG.
  • the controller 112 is coupled to the detector 118 and the radiation source 115.
  • the control radiation source 115 emits a beam 116 as the inspection aircraft 113 passes through the scanning area formed by the radiation source and the detector, and controls the detector.
  • the radiation from the radiation source 115 that penetrates the inspected aircraft 113 is received to obtain an output signal.
  • the image generation module 111 is, for example, an imaging computer that receives the output signal and generates a top view transmission image of the inspected aircraft 113 based on the output signal.
  • the gantry 121 has a sliding rail 114 that allows the ray source 115 to move along the sliding rail 114, such as to a position 119 on the right or left side, and the detector can
  • the guide rails in the trench are slid in synchronism with the radiation source 115, for example to a corresponding position 120 on the right or left side.
  • the controller 112 controls the radiation source 115 to move to one side along the slide rail 114, and controls the detector 118 to move synchronously to the side, thereby being inspected by the aircraft 113 being inspected.
  • the side is subjected to a transmission inspection.
  • the ray source and the detector perform linear motion in the same direction only on the guide rail, for example, the direction perpendicular to the moving direction of the aircraft, it is easy to control the synchronism.
  • the detector is placed in the trench, the aircraft can pass directly from above, saving scanning time and there is no scanning blind zone.
  • the detector is placed in the trench, and the surface of the detector or the upper surface of the detector cover is coplanar with the ground.
  • the ray source and detector can be moved synchronously very easily during scan inspections, allowing quick inspection of the aircraft's wings and larger aircraft.
  • the radiation source 115 when scanning the aircraft 113 being inspected, the radiation source 115 generates a high-energy X/Gamma ray pulse that penetrates the inspected aircraft 113, and the high-sensitivity detector array receives the X/Gamma ray and converts it into an output signal. .
  • the image generation module 111 automatically generates a complete transmission image of the aircraft being inspected.
  • the source of radiation used in the above embodiments is a linear accelerator (or other type of source) that is fixed in the air by a steel support structure that is placed in a trench that is coplanar with the beam source.
  • the aircraft is unmanned, and the drag device pulls the aircraft through the beam and ensures that the drag device does not damage the aircraft.
  • the detector receives X/Gamma rays that pass through the aircraft and converts them into output signals. When the entire scanning process is over, the image generation module 111 will generate a top view scan image of the aircraft.
  • the source 115 and detector 118 can be moved perpendicular to the aircraft within the steel frame structure and the trench, respectively. Make a relatively static movement in the direction to scan different parts of the aircraft.
  • the ray source 115 scans the aircraft at one, two or more locations (e.g., three locations as shown in Figure 1) to complete the scanning of the entire fuselage, and the detector follows the ray source to move synchronously, ensuring that it is always in The corresponding position below the accelerator.
  • the length of the detector can be set to be less than or equal to one-half of the width of the gantry 121, such as setting the length of the detector to one-third or four-minutes of the width of the gantry 121. one.
  • the scanning of the entire aircraft can be completed by increasing the number of round trips of the aircraft.
  • Fig. 2 is a view showing the configuration of a system for performing a security check on an aircraft according to another embodiment of the present invention.
  • the detector 118 is entirely fixed in the trench 117 and does not slide in the trench.
  • the length of the detector should be set to be greater than or equal to the width of the gantry 121.
  • only the source 115 is moved laterally to the left and right positions 119 as needed to complete the transmission scan of the aircraft as a whole.
  • FIG. 3 is a block diagram showing the construction of a system for performing a security check on an aircraft according to still another embodiment of the present invention.
  • three ray sources 1191, 1192 and 1193 having coherent beams are arranged on the support, respectively emitting X-ray beams or Gamma ray beams 1161, 1162 downward.
  • the illustrated system for inspecting an aircraft includes three sources 1191, 1192, and 1193, a gantry 121, a detector 118 in the trench 7, a controller 112, and an image generation module 111.
  • the gantry 8 carries the three sources of radiation whose beam currents are coplanar and correspond to detectors in the trench.
  • Detector 118 is disposed in a trench 117 that is coplanar with the beam of radiation from the source.
  • the controller 112 is coupled to the detector and the three radiation sources, and controls the three radiation sources to emit a beam of rays when the inspected aircraft passes through the scanning area formed by the three radiation sources and the detector, and The detector is controlled to receive radiation from the three radiation sources that penetrates the inspected aircraft to obtain an output signal.
  • the image generation module 111 receives the output signal and generates a top view transmission image of the inspected aircraft based on the output signal.
  • the solution of the above embodiment can speed up the safety inspection of the aircraft, and the entire body can be scanned by the aircraft once through the scanning area.
  • those skilled in the art can set fewer or more sources of radiation depending on the application.
  • those skilled in the art can set fewer or more sources of radiation depending on the application.
  • only two radiation sources 1191 and 1192 are included in the embodiment shown in Figure 4 to save cost.
  • the source 115 emits a first beam of a first energy and a second beam of a second energy, such as a first beam of light being a 3 MeV low energy beam and a second beam of 6 MeV or 9 MeV being high.
  • the detector 118 receives the first beam and the second beam.
  • the image generation module 111 receives the output signals of the first detection array and the second detection array to generate a dual-energy transmission image of the inspected aircraft 113. In this case, the image generation module 111 outputs a dual-energy image of the aircraft being inspected.
  • detector 118 includes a plurality of detector arrays corresponding to different portions of a beam of radiation, for example, a first detection array that includes a first portion of the beam (eg, a lower energy portion) And a second detection array disposed below the first detector array and responsive to a second portion of the same beam, such as a portion of higher energy.
  • the image generation module 111 receives the output signals of the first detection array and the second detection array to generate a dual-energy transmission image of the inspected aircraft 113. In this case, the image generation module 111 outputs a pseudo dual energy image of the aircraft being inspected.
  • the source 115 emits a first angular beam 122 and a second angular beam 124, and said detectors are disposed at respective predetermined intervals in substantially parallel with the gantry 121.
  • the first angle detection array 123 and the second angle detection array 125 in the trench receive the first angle beam 122 and the second angle beam 124 that penetrate the inspected aircraft 113, respectively, and the image generation module 111 receives the first angle detection array
  • the output signals of the array 125 and the second angle detection array 125 thereby generate a dual view transmission image of the aircraft 113 being inspected.
  • the height of the gantry is adjustable.
  • a computer program eg, implemented as one or more programs running on one or more computer systems
  • implemented as one or more programs running on one or more processors eg, implemented as one or One or more programs running on a plurality of microprocessors, implemented as firmware, or substantially in any combination of the above, and those skilled in the art, in accordance with the present disclosure, will be provided with design circuitry and/or write software and / or firmware code capabilities.
  • processors eg, implemented as one or One or more programs running on a plurality of microprocessors, implemented as firmware, or substantially in any combination of the above, and those skilled in the art, in accordance with the present disclosure, will be provided with design circuitry and/or write software and / or firmware code capabilities.
  • the mechanisms of the subject matter disclosed herein can be distributed as a variety of forms of program products, and regardless of the particular type of signal bearing medium that is actually used to perform the distribution, the subject matter of the present disclosure
  • the exemplary embodiments are applicable.
  • Sample package for signal bearing media And but not limited to: Recordable media such as floppy disks, hard drives, compact discs (CDs), digital versatile discs (DVDs), digital tapes, computer memory, etc.; and transmission-type media such as digital and/or analog communication media (eg, fiber optic cable, waveguide, wired communication link, wireless communication link, etc.).
  • Recordable media such as floppy disks, hard drives, compact discs (CDs), digital versatile discs (DVDs), digital tapes, computer memory, etc.
  • transmission-type media such as digital and/or analog communication media (eg, fiber optic cable, waveguide, wired communication link, wireless communication link, etc.).

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Abstract

公开了对飞机进行检查的系统和方法。射线源和探测器分别位于飞机机身的上方和下方，射线源产生射线束，穿透被检查飞机，探测器接收穿透被检查飞机的射线束并将其转换成输出信号，实时地产生俯视透射图像。

Description

对飞机进行检査的系统和方法 技术领域
本发明的实施例涉及以飞机为被检物件的射线安全检查系统。 背景技术
目前还没有专门为飞机检查设计的扫描系统， 现有的 X/Gamma射线的安全 检查系统中， 只有基于背散射原理的扫描系统可用于飞机扫描。 背散射原理是将射 线源和探测器置于被检物的同侧， 射线源发射出的 X/Gamma粒子入射到被检物， 一部分粒子被被检物吸收； 未被吸收的粒子则与被检物发生散射， 当散射角小于 90 度时， 散射光子穿透被检物， 当散射角大于 90度时， 散射光子从入射一侧被弹回。 背散射技术就是将射线源和探测器置于被检物的同侧，以探测散射角大于 90度的背 散射光子。
背散射产品占地面积小， 使用灵活。 但是该类扫描系统不是专门针对飞机检 查而设计的， 在应用于飞机扫描的过程中有一些局限性。 背散射扫描系统的射线能 量低， 穿透力不足， 无法穿透机翼和机身进行完整而彻底的检查。 特别是在被检物 接近射线源位置为低 Z物质的情况下， 射线与低 Z物质发生大角度散射， 很多粒子 被弹回， 不能深入到被检物内部， 无法深入检查。 对于飞机检测而言， 背散射类产 品通常基于可移动的车载平台， 无法全面的检查到飞机的所有部位， 如距地面较高 (尾翼） 或较低 （公务飞机的底部） 的位置。 另外， 基于车载的背散射类检测系统 在用于飞机扫描时， 需要将设备沿机身和两侧机翼移动， 扫描效率较低。 发明内容
针对现有技术中的一个或多个问题， 提出了一种对飞机进行检查的系统。 在本发明的一个方面， 提出了一种飞机检查系统， 包括： 门架； 射线源， 用 于发出射线束， 所述射线源位于所述门架上且可在所述门架上移动； 探测器， 用 于接收射线束并转换成输出信号， 所述探测器设置在与所述射线源的射线束共面 的地沟中； 控制器， 与所述探测器和所述射线源连接， 控制所述射线源在被检查 飞机移动穿过所述射线源和所述探测器构成的扫描区域时发出射线束， 并且控制 所述探测器接收所述射线源发出的穿透被检查飞机的射线束； 图像生成模块， 用 于接收所述探测器的输出信号从而生成被检查飞机的俯视透射图像。
优选地， 所述门架具有滑动导轨， 允许所述射线源沿着滑动导轨移动， 并 且所述探测器能够与所述射线源同步地沿着地沟中的导轨滑动； 所述控制器控制 所述射线源沿着滑动导轨向一侧移动至预定位置， 并且控制所述探测器同步地向 该侧移动至与该预定位置相应的位置， 从而对所述被检查飞机的所述侧进行透射 检查。
优选地， 所述探测器的长度小于或等于门架宽度的二分之一。
优选地， 所述射线源具体为加速器或者放射源， 产生 X 射线或者 Gamma 射线。
优选地，所述探测器具体包括 X射线或 Gamma射线灵敏的气体或固体探测 器°
优选地， 所述探测器固定在地沟中。
优选地， 所述门架具有滑动导轨， 允许所述射线源沿着滑动导轨移动； 所 述控制器控制所述射线源沿着滑动导轨向一侧移动， 从而对所述被检查飞机的所 述侧进行透射检查。
优选地， 所述探测器的长度大于等于所述门架的宽度三分之二。
优选地， 所述射线源发出第一能量的第一射线束和第二能量的第二射线束， 所述探测器接收第一射线束和第二射线束， 所述图像生成模块接收所述探测器的 输出信号从而生成被检查飞机的双能透射图像。
优选地， 所述探测器包括对一射线束中的第一部分做出反应的第一探测阵 列和设置在第一探测阵列下面并且对该射线束的第二部分做出反应的第二探测 阵列， 所述图像生成模块接收所述第一探测阵列和第二探测阵列的输出信号从而 生成被检查飞机的双能透射图像。
优选地， 所述射线源发出第一角度射线束和第二角度射线束， 并且所述探 测器包括与门架基本上平行地以预定的间隔设置在各自的地沟中的第一角度探 测阵列和第二角度探测阵列， 分别接收穿透被检查飞机的第一角度射线束和第二 角度射线束， 所述图像生成模块接收所述第一角度探测阵列和第二角度探测阵列 的输出信号从而生成被检查飞机的双视角透射图像。
优选地， 所述门架的高度是可调节的。
在本发明的另一方面， 提出了一种飞机检查方法， 包括： 从设置于门架上的 射线源发出射线束， 所述射线源位于所述门架上且可在所述门架上移动； 通过设 置在与所述射线源的射线束共面的地沟中的探测器接收射线束并转换成输出信 号； 控制所述射线源在被检查飞机移动穿过所述射线源和所述探测器构成的扫描 区域时发出射线束， 并且控制所述探测器接收所述射线源发出的穿透被检查飞机 的射线束； 接收所述探测器的输出信号从而生成被检查飞机的俯视透射图像。
优选地， 所述的方法还包括步骤： 控制所述射线源沿着滑动导轨向一侧移 动至预定位置， 并且控制所述探测器同步地向该侧移动至与该预定位置相应的位 置， 从而对所述被检查飞机的所述侧进行透射检查。
在本发明的又一方面， 提出了一种对飞机进行检查的系统， 包括： 门架； 至少两个射线源， 发出射线束， 并且所述至少两个射线源位于所述门架上且它们 发出的射线束流共面； 探测器， 用于接收射线束并转换成输出信号， 所述探测器 设置在与所述射线源的射线束流共面的地沟中； 控制器， 与所述探测器和所述至 少两个射线源连接， 控制所述至少两个射线源在被检查飞机穿过所述至少两个射 线源和探测器构成的扫描区域时发出射线束， 并且控制所述探测器接收所述至少 两个射线源发出的穿透被检查飞机的射线束； 以及图像生成模块， 用于接收所述 探测器的输出信号从而生成被检查飞机的俯视透射图像。
根据上述实施例的方案， 能够对飞机进行较快并且准确的透射安全检查。 附图说明
下面的附图表明了本发明的实施方式。 这些附图和实施方式以非限制性、 非穷举性的方式提供了本发明的一些实施例， 其中：
图 1 示出了根据本发明一个实施例的对飞机进行检查的系统的结构示意 图；
图 2示出了根据本发明另一实施例的对飞机进行安全检查的系统的结构示 意图；
图 3示出了根据本发明再一实施例的对飞机进行安全检查的系统的结构示 意图；
图 4示出了根据本发明又一实施例的对飞机进行安全检查的系统的结构示 意图； 以及
图 5示出了根据本发明其他实施例的对飞机进行安全检查的系统的结构示 意图。
附图标记：
110： 地面； 111 : 图像生成模块 111 ; 112： 控制器； 113 : 被检查飞机； 114： 滑动导轨； 115 : 射线源 116: 射线束； 117 : 地沟； 118 : 探测器； 119: 加 速器向两侧移动后的扫描位置； 120探测器向两侧移动后的位置； 121：门架； 122： 射线束； 123 ; 探测器； 124 : 射线束； 125 : 探测器。 具体实施方式
下面将详细描述本发明的具体实施例， 应当注意， 这里描述的实施例只用于 举例说明， 并不用于限制本发明。在以下描述中， 为了提供对本发明的透彻理解， 阐述了大量特定细节。 然而， 对于本领域普通技术人员显而易见的是： 不必采用 这些特定细节来实行本发明。 在其他实例中， 为了避免混淆本发明， 未具体描述 公知的结构、 电路、 材料或方法。
在整个说明书中， 对"一个实施例"、 "实施例"、 "一个示例"或"示例"的提及 意味着： 结合该实施例或示例描述的特定特征、 结构或特性被包含在本发明至少 一个实施例中。 因此， 在整个说明书的各个地方出现的短语"在一个实施例中"、 "在实施例中"、 "一个示例"或"示例"不一定都指同一实施例或示例。 此外， 可以 以任何适当的组合和 /或子组合将特定的特征、结构或特性组合在一个或多个实施 例或示例中。 此外， 本领域普通技术人员应当理解， 这里使用的术语"和 /或"包括 一个或多个相关列出的项目的任何和所有组合。
根据一些实施例的方案， 将射线源和探测器分别位于飞机机身的上方和下 方， 射线源产生 X/Gamma射线， 穿透被检飞机， 探测器阵列接受 X/Gamma射线 转换成输出信号， 并实时地产生俯视透射图像。
图 1示出了根据本发明一个实施例的对飞机进行检查的系统的结构示意图。 如图 1所示的系统包括射线源 115、 门架 121、 探测器 118、 控制器 112和图像生 成模块 111。 射线源 115， 例如为 X射线源或者 Gamma射线源， 发出射线束。 门 架 121承载射线源 115， 使得射线源 115向下发射 X射线束。 探测器 115设置在 与所述射线源的射线束流共面的地沟中， 例如图 1所示的地面 110的地沟中。
控制器 112与探测器 118以及射线源 115连接，控制射线源 115在被检查飞 机 113穿过射线源和探测器构成的扫描区域时发出射线束 116， 并且控制探测器 接收射线源 115发出的穿透被检查飞机 113的射线， 得到输出信号。 图像生成模 块 111例如为成像计算机， 它接收所述输出信号， 并且根基于所述输出信号产生 所述被检查飞机 113的俯视透射图像。
根据图示的实施例中， 所述门架 121 具有滑动导轨 114， 允许所述射线源 115沿着滑动导轨 114移动， 例如移动到右侧或左侧的位置 119， 并且所述探测 器能够沿着地沟中的导轨与射线源 115同步地滑动， 例如移动到右侧或左侧的相 应位置 120。 在这种情况下， 所述控制器 112控制所述射线源 115沿着滑动导轨 114向一侧移动， 并且控制所述探测器 118同步地向该侧移动， 从而对所述被检 查飞机 113的所述侧进行透射检查。
这样， 由于射线源和探测器仅在导轨上做同一个方向上的直线运动， 比如 垂直于飞机移动方向的方向， 易于控制同步性好。 此外， 探测器设置在地沟中， 飞机可以直接从上方通过， 节约扫描时间还不存在扫描盲区。
另外， 探测器设置在地沟中， 探测器表面或者探测器保护盖板上表面与地 面共面， 当飞机从探测器上方通过时， 运行稳定无起伏。 此外， 在进行扫描检查 工作时， 射线源和探测器可以非常容易的进行同步移动， 可以快速检查飞机的机 翼和体积较大的飞机。
根据上述实施例， 在对被检查飞机 113 进行扫描时， 射线源 115 产生高能 X/Gamma射线脉冲， 穿透被检查飞机 113， 高灵敏度探测器阵列接收 X/Gamma射 线并将之转换成输出信号。 当整个扫描过程结束时， 图像生成模块 111 自动生成被 检飞机的完整透射图像。
上述实施例中使用的射线源为直线加速器 （或其他类型射线源） ， 通过钢支 架结构固定在空中， 探测器阵列放置在与射线源束流共面的地沟中。 飞机为无人驾 驶状态， 拖动装置牵引飞机经过射线束流， 且保证拖动装置对飞机无损伤。 探测器 接收到穿过飞机的 X/Gamma射线转换成输出信号。 当整个扫描过程结束时， 图像 生成模块 111将生成飞机的俯视扫描图像。 若加速器的束流张角不能一次覆盖整个 飞机， 为保证对整个飞机的扫描 （机身、 机翼和尾翼） ， 射线源 115和探测器 118 可分别在钢架结构和地沟内在垂直于飞机移动方向上做相对静止的移动以扫描飞机 的不同部位。 射线源 115在一个、 两个或多个位置 （例如图 1所示的三个位置） 对 飞机进行扫描， 以完成对整个机身的扫描， 探测器跟随射线源同步移动， 保证其总 是处于加速器下方相应的位置。在图 1所示的实施例中， 出于探测器成本与飞机往 返扫描次数的平衡考虑， 可以将探测器的长度设置成小于或等于门架 121的宽度 的二分之一，比如将探测器的长度设置成门架 121的宽度的三分之一或四分之一。 在这探测器长度远小于门架的宽度的情况下， 增加飞机往返的扫描次数就能完成 整个飞机的扫描检查。
图 2示出了根据本发明另一实施例的对飞机进行安全检查的系统的结构示 意图。 如图 2所示的方案中， 探测器 118整个固定在地沟 117之中， 并不在地沟 中滑动。 在这种情况下， 由于探测器是固定在地沟中的， 并不在地沟中滑动， 为 了能够完成对整个飞机的透视扫描， 应当将探测器的长度设置成大于或等于门架 121 宽度的三分之二， 或者基本上与门架的宽度相等。 在图示的实施例中， 仅仅 射线源 115在需要的情况下横向移动到左右两侧的位置 119， 从而完成对飞机的 整体上的透射扫描。 图 3示出了根据本发明再一实施例的对飞机进行安全检查的 系统的结构示意图。 在图示的实施例中， 为了获得更快的检查速度， 在支架上设 置了束流共面的三个射线源 1191、 1192和 1193， 分别向下发射 X射线束或者 Gamma射线束 1161、 1162和 1163。 图示的对飞机进行检查的系统包括三个射线 源 1191、 1192和 1193， 门架 121， 地沟 7中的探测器 118， 控制器 112和图像生 成模块 111。 在图示的实施例中门架 8承载所述三个射线源， 这些射线源的射线 束流共面， 与地沟中的探测器对应。
探测器 118设置在与所述射线源的射线束流共面的地沟 117中。控制器 112 与所述探测器和所述三个射线源连接， 控制所述三个射线源在被检查飞机穿过所 述三个射线源和探测器构成的扫描区域时， 发出射线束， 并且控制所述探测器接 收所述三个射线源发出的穿透被检查飞机的射线， 得到输出信号。 图像生成模块 111， 接收所述输出信号， 并且根基于所述输出信号产生所述被检查飞机的俯视 透射图像。
上述实施例的方案可以使得对飞机的安全检查速度得到加快， 飞机一次通 过扫描区域就可以完成对整个机身的扫描。
在其他实施例中， 本领域的技术人员可以根据不同的应用设置较少或者更 多的射线源。 例如， 在图 4所示的实施例中仅仅包括两个射线源 1191和 1192， 以节约成本。
在一些实施例中， 射线源 115 发出第一能量的第一射线束和第二能量的第 二射线束， 如第一射线束为 3MeV低能射线束， 第二射线束为 6MeV或 9MeV高 能射线束。 而探测器 118接收第一射线束和第二射线束。 这种情况下图像生成模 块 111接收第一探测阵列和第二探测阵列的输出信号从而生成被检查飞机 113的 双能透射图像。 这种情况下， 图像生成模块 111输出被检查飞机的双能图像。
在一些实施例中， 探测器 118 包括对一个射线束的不同部分作出相应的多 个探测器阵列， 例如包括对射线束的第一部分 （如能量较低的部分） 做出反应的 第一探测阵列和设置在第一探测器阵列下面并且对同一射线束的第二部分（如能 量较高的部分） 做出反应的第二探测阵列。 在这种情况下， 图像生成模块 111接 收所述第一探测阵列和第二探测阵列的输出信号从而生成被检查飞机 113的双能 透射图像。 在这种情况下， 图像生成模块 111输出被检查飞机的伪双能图像。
如图 5所示的实施例中， 射线源 115发出第一角度射线束 122和第二角度 射线束 124， 并且所述探测器包括与门架 121基本上平行地以预定的间隔设置在 各自的地沟中的第一角度探测阵列 123和第二角度探测阵列 125， 分别接收穿透 被检查飞机 113的第一角度射线束 122和第二角度射线束 124，图像生成模块 111 接收第一角度探测阵列 123和第二角度探测阵列 125的输出信号从而生成被检查 飞机 113的双视角透射图像。 在一些实施例中， 所述门架的高度是可调节的。 以上的详细描述通过使用示意图和 /或示例， 已经阐述了检查飞机的系统及方 法的众多实施例。 在这种示意图和 /或示例包含一个或多个功能和 /或操作的情况 下，本领域技术人员应理解，这种示例中的每一功能和 /或操作可以通过各种硬件、 软件、 固件或实质上它们的任意组合来单独和 /或共同实现。 在一个实施例中， 本 发明的实施例所述主题的若干部分可以通过专用集成电路 （ASIC )、 现场可编程 门阵列 （FPGA)、 数字信号处理器 （DSP)、 或其他集成格式来实现。 然而， 本领 域技术人员应认识到， 这里所公开的实施例的一些方面在整体上或部分地可以等 同地实现在集成电路中， 实现为在一台或多台计算机上运行的一个或多个计算机 程序（例如， 实现为在一台或多台计算机系统上运行的一个或多个程序）， 实现为 在一个或多个处理器上运行的一个或多个程序 （例如， 实现为在一个或多个微处 理器上运行的一个或多个程序）， 实现为固件， 或者实质上实现为上述方式的任意 组合， 并且本领域技术人员根据本公开， 将具备设计电路和 /或写入软件和 /或固 件代码的能力。 此外， 本领域技术人员将认识到， 本公开所述主题的机制能够作 为多种形式的程序产品进行分发， 并且无论实际用来执行分发的信号承载介质的 具体类型如何， 本公开所述主题的示例性实施例均适用。 信号承载介质的示例包 括但不限于： 可记录型介质， 如软盘、 硬盘驱动器、 紧致盘 （CD )、 数字通用盘 (DVD )、 数字磁带、 计算机存储器等； 以及传输型介质， 如数字和 /或模拟通信 介质 （例如， 光纤光缆、 波导、 有线通信链路、 无线通信链路等）。
虽然已参照几个典型实施例描述了本发明， 但应当理解， 所用的术语是说明 和示例性、 而非限制性的术语。 由于本发明能够以多种形式具体实施而不脱离发 明的精神或实质， 所以应当理解， 上述实施例不限于任何前述的细节， 而应在随 附权利要求所限定的精神和范围内广泛地解释， 因此落入权利要求或其等效范围 内的全部变化和改型都应为随附权利要求所涵盖。

Claims

权利要求
1、 一种对飞机进行检查的系统， 包括：
门架；
射线源， 用于发出射线束， 所述射线源位于所述门架上且可在所述门架上移 动；
探测器， 用于接收射线束并转换成输出信号， 所述探测器设置在与所述射线 源的射线束共面的地沟中；
控制器， 与所述探测器和所述射线源连接， 控制所述射线源在被检查飞机移 动穿过所述射线源和所述探测器构成的扫描区域时发出射线束， 并且控制所述探 测器接收所述射线源发出的穿透被检查飞机的射线束；
图像生成模块， 用于接收所述探测器的输出信号从而生成被检查飞机的俯 视透射图像。
2、 如权利要求 1所述的系统， 其中， 所述门架具有滑动导轨， 允许所述射 线源沿着滑动导轨移动， 并且所述探测器能够与所述射线源同步地沿着地沟中的 导轨滑动；
所述控制器控制所述射线源沿着滑动导轨向一侧移动至预定位置， 并且控 制所述探测器同步地向该侧移动至与该预定位置相应的位置， 从而对所述被检查 飞机的所述侧进行透射检查。
3、 如权利要求 2所述的系统， 其中， 所述探测器的长度小于或等于门架宽 度的二分之一。
4、 如权利要求 1所述的系统， 其中所述射线源具体为加速器或者放射源， 产生 X射线或者 Gamma射线。
5、 如权利要求 1所述的系统， 其中所述探测器具体包括 X射线或 Gamma 射线灵敏的气体或固体探测器。
6、 如权利要求 1所述的系统， 其中所述探测器固定在地沟中。
7、 如权利要求 6所述的系统， 其中所述门架具有滑动导轨， 允许所述射线 源沿着滑动导轨移动；
所述控制器控制所述射线源沿着滑动导轨向一侧移动， 从而对所述被检查 飞机的所述侧进行透射检查。
8、 如权利要求 6所述的系统， 其中所述探测器的长度大于等于所述门架的 宽度三分之二。
9、 如权利要求 1所述的系统， 其中所述射线源发出第一能量的第一射线束 和第二能量的第二射线束， 所述探测器接收第一射线束和第二射线束， 所述图像 生成模块接收所述探测器的输出信号从而生成被检查飞机的双能透射图像。
10、 如权利要求 1 所述的系统， 其中所述探测器包括对一射线束中的第一 部分做出反应的第一探测阵列和设置在第一探测阵列下面并且对该射线束的第 二部分做出反应的第二探测阵列， 所述图像生成模块接收所述第一探测阵列和第 二探测阵列的输出信号从而生成被检查飞机的双能透射图像。
11、 如权利要求 1 所述的系统， 其中所述射线源发出第一角度射线束和第 二角度射线束， 并且所述探测器包括与门架基本上平行地以预定的间隔设置在各 自的地沟中的第一角度探测阵列和第二角度探测阵列， 分别接收穿透被检查飞机 的第一角度射线束和第二角度射线束， 所述图像生成模块接收所述第一角度探测 阵列和第二角度探测阵列的输出信号从而生成被检查飞机的双视角透射图像。
12、 如权利要求 1所述的系统， 其中所述门架的高度是可调节的。
13、 一种对飞机进行检查的方法， 包括：
从设置于门架上的射线源发出射线束， 所述射线源位于所述门架上且可在所 述门架上移动；
通过设置在与所述射线源的射线束共面的地沟中的探测器接收射线束并转 换成输出信号；
控制所述射线源在被检查飞机移动穿过所述射线源和所述探测器构成的扫 描区域时发出射线束， 并且控制所述探测器接收所述射线源发出的穿透被检查飞 机的射线束；
接收所述探测器的输出信号从而生成被检查飞机的俯视透射图像。
14、 如权利要求 13所述的方法， 还包括步骤：
控制所述射线源沿着滑动导轨向一侧移动至预定位置， 并且控制所述探测 器同步地向该侧移动至与该预定位置相应的位置， 从而对所述被检查飞机的所述 侧进行透射检查。
15、 一种对飞机进行检查的系统， 包括：
门架； 至少两个射线源， 发出射线束， 并且所述至少两个射线源位于所述门架上 且它们发出的射线束流共面；
探测器， 用于接收射线束并转换成输出信号， 所述探测器设置在与所述射 线源的射线束流共面的地沟中；
控制器， 与所述探测器和所述至少两个射线源连接， 控制所述至少两个射 线源在被检查飞机穿过所述至少两个射线源和探测器构成的扫描区域时发出射 线束， 并且控制所述探测器接收所述至少两个射线源发出的穿透被检查飞机的射 线束； 以及
图像生成模块， 用于接收所述探测器的输出信号从而生成被检查飞机的俯视透射 图像。
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