CN111522047A - Space-borne space photoelectric conversion module and photoelectric detection device - Google Patents
Space-borne space photoelectric conversion module and photoelectric detection device Download PDFInfo
- Publication number
- CN111522047A CN111522047A CN202010212141.5A CN202010212141A CN111522047A CN 111522047 A CN111522047 A CN 111522047A CN 202010212141 A CN202010212141 A CN 202010212141A CN 111522047 A CN111522047 A CN 111522047A
- Authority
- CN
- China
- Prior art keywords
- space
- hole
- crystal
- flange
- photoelectric conversion
- Prior art date
- Legal status (The legal status 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 status listed.)
- Granted
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01T—MEASUREMENT OF NUCLEAR OR X-RADIATION
- G01T1/00—Measuring X-radiation, gamma radiation, corpuscular radiation, or cosmic radiation
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01K—MEASURING TEMPERATURE; MEASURING QUANTITY OF HEAT; THERMALLY-SENSITIVE ELEMENTS NOT OTHERWISE PROVIDED FOR
- G01K7/00—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements
- G01K7/16—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements
- G01K7/22—Measuring temperature based on the use of electric or magnetic elements directly sensitive to heat ; Power supply therefor, e.g. using thermoelectric elements using resistive elements the element being a non-linear resistance, e.g. thermistor
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01T—MEASUREMENT OF NUCLEAR OR X-RADIATION
- G01T7/00—Details of radiation-measuring instruments
- G01T7/005—Details of radiation-measuring instruments calibration techniques
Abstract
The invention provides a space-borne space photoelectric conversion module and a photoelectric detection device, wherein the photoelectric detection device comprises an array formed by photoelectric detection units, each photoelectric detection unit comprises a crystal module and a photoelectric conversion module, each photoelectric conversion module comprises a photoelectric converter, an electronics reading circuit board and a protection structure, each protection structure comprises an inner bushing, a magnetic shielding device and an outer bushing, the inner bushing and the outer bushing are made of magnesium-aluminum alloy materials, and the magnetic shielding devices are made of permalloy sheets. According to the invention, through structural improvement, the crystal module/the photoelectric conversion module are relatively independent, the problem of convenience in replacement of the satellite-borne crystal and the photoelectric conversion module can be solved, the inheritance of aerospace products is improved, the development period is shortened, the detection device can meet the requirement of the launching environment through the examination of the space mechanics environment, and the structural quality of equipment is effectively reduced through the integrated compact design on the premise of ensuring the structural strength.
Description
Technical Field
The invention belongs to the technical field of space detection, and particularly relates to a satellite-borne space photoelectric conversion module and a photoelectric detection device.
Background
Detecting spatially energetic particles requires structures with high energy resolution and high reliability, and should be of low mass. The prior detectors in China generally belong to carrying, and since the space science leading special item of Chinese academy of sciences is started, special scientific detection loads are gradually provided, but materials used by a photoelectric detection unit part are also hard aluminum alloy, and the quality is still large.
Meanwhile, the special development of space solar detection by using satellites is the first time in China, and different from RHESSI satellites (adopting Ge detectors, reference RHESSI websites), YOHKOH satellites (adopting NaI for HXT) in Japan and SolarOrbiter satellites (adopting CdZnTe for STIX) in European space Bureau, LaBr is adopted in the design3The crystal detector is used for solar hard X-ray detection, has the characteristics of high energy resolution, fast time response and the like, and simultaneously has various problems in the aspects of ground self-protection, on-orbit self-calibration and the like.
Disclosure of Invention
The technical purpose of the invention is to design a special satellite-borne space photoelectric conversion module and a detection device, to improve the compactness and the integrity of the device structure, reduce the structure quality of the detection device and provide a better electromagnetic shielding effect by reasonable planning and improvement on the premise of ensuring the structural strength and the rigidity, to ensure that on-rail temperature monitoring can be carried out (compensation and correction of space scientific data are carried out by using ground calibration data later) and to ensure the stability of space detection of the photoelectric detection device.
The technical scheme of the invention is as follows:
the utility model provides a space-borne space photoelectric conversion module which characterized in that, includes photoelectric conversion device, electronics reading circuit board and protective structure:
the protective structure comprises an inner bushing, a magnetic shielding device and an outer bushing, wherein the inner bushing and the outer bushing are both made of magnesium-aluminum alloy materials, and the magnetic shielding device is made of permalloy sheets;
the magnetic shielding device wraps the outer side of the inner lining, and the top and the bottom of the magnetic shielding device respectively abut against the small flanges at the upper end and the lower end of the inner lining; the side wall of the inner bushing is provided with a through hole groove, so that the buffer glue filled into the inner bushing seeps out through the through hole groove and contacts with the magnetic shielding device, the contact friction force of the magnetic shielding device is improved, and the magnetic shielding device is prevented from rotating inside;
the outer sleeve includes a sleeve and a bracket connection structure;
the inner bushing wrapped by the magnetic shielding device is arranged in the sleeve of the outer bushing, the upper edge of the opening of the sleeve of the outer bushing is higher than the upper edge of the opening of the inner bushing, and gaps among the photoelectric conversion device, the inner bushing and the side wall of the outer bushing are filled with buffer glue;
the support connecting structure comprises a first flange arranged at the bottom of the sleeve, a second flange arranged in the middle or at the upper part of the sleeve and a mounting support fixed on the second flange, the mounting support is of a frame type structure, and the electronic reading circuit board is fixed at the top end of the mounting support and is electrically connected with a photoelectric conversion device below the electronic reading circuit board;
the size of the first flange is larger than that of the small flanging at the bottom end of the inner liner, when the inner liner is assembled, the upper surface of the small flanging at the bottom end of the inner liner abuts against the lower surface of the first flange and is used for installing and positioning the inner liner, the first flange is simultaneously provided with a first butt joint hole for connecting a crystal module, and the first butt joint hole is positioned at the periphery of the small flanging at the bottom end in the radial direction;
and a reserved through hole for the screwdriver to pass through is formed in the second flange at the position corresponding to the first butt hole.
On the basis of the above scheme, a further improved or preferred scheme further comprises:
the mounting bracket comprises four upright posts which are arranged in a rectangular shape, three adjacent upright posts are connected through a cross beam, boss flanges which are bent upwards and inwards are arranged on the cross beam, and the limiting blocking of the electronic reading circuit board is carried out through the boss flanges in three directions for preliminary positioning before fixing; a heat conduction support is arranged above the electronics reading circuit board, a board body at the edge part of the electronics reading circuit board after initial positioning is as high as the upper surface of a lug boss flanging, so that the heat conduction support is in contact with the edge part of the electronics reading circuit board, meanwhile, the lug boss flanging corresponding to the edge part is also in contact, namely, the contact area of the detection unit and the heat conduction support is increased through the lug boss flanging, and the heat conduction efficiency is improved.
The photoelectric conversion module is provided with a temperature sensor for monitoring the photoelectric conversion module, and the temperature sensor is arranged on a lug boss turning edge which is not contacted with the heat conduction support on the electronics reading circuit board or on the first flange. When the temperature sensor is arranged on the lug boss flanging, the temperature sensor is fixed in the temperature sensor mounting hole on the lug boss flanging; when the temperature sensor is installed on the first flange, the temperature sensor is fixed in the temperature sensor installation hole on the first flange, and the second flange is provided with a threading hole at the position corresponding to the temperature sensor installation hole.
And a second butt joint hole for connecting an external complete machine is arranged on the second flange, and the second butt joint hole is positioned on the periphery of the first flange in the radial direction.
The thickness of the permalloy sheet is 0.027mm, and three circles are wrapped on the inner lining.
A space-borne space photoelectric detection device is provided with an array consisting of a plurality of photoelectric detection units, wherein each photoelectric detection unit consists of a crystal module and a photoelectric conversion module, and the crystal module comprises a crystal, a crystal protection structure, a temperature detection structure and a performance calibration structure;
the crystal protection structure comprises a tube shell, an end cover and a quartz glass sheet for sealing;
the crystal-silicon crystal shell comprises a shell, wherein the shell is T-shaped and comprises a rectangular block-shaped head and a cylindrical lower tube body which are integrally formed, a cylindrical main body shell cavity is arranged at the center of the shell, a crystal is installed in the main body shell cavity, an end cover is sleeved at the bottom end of the shell and is in sealing connection with the shell, and a bottom port of the main body shell cavity is blocked;
the upper end of the head of the tube shell is provided with a third butt joint hole with an upward opening corresponding to the position of the first butt joint hole of the photoelectric detection module, and the third butt joint hole is matched with the first butt joint hole in the butt joint of the crystal module and the photoelectric detection module for use to fasten the connection of the crystal module and the photoelectric detection module; the lower end of the head of the pipe shell is provided with a fourth butt joint hole with a downward opening, the fourth butt joint hole is used for being connected with an external complete machine, and the third butt joint hole and the fourth butt joint hole are counter bores;
the top surface of the head of the tube shell is provided with a through hole groove for glue filling and an annular flange protruding inwards, the annular flange is positioned between the through hole groove and the main body shell cavity, the diameter of the through hole groove is larger than that of the main body shell cavity, and the diameter of the main body shell cavity is larger than that of a central through hole of the annular flange;
the quartz glass sheet is arranged at the top end of the crystal, the lower surface of the quartz glass sheet is attached to the top surface of the crystal, the edge part of the upper surface of the quartz glass sheet is hermetically connected with the lower surface of the annular flange to block a top port of the main body shell cavity, and a gap between the crystal and the shell and the end cover is filled with optical coupling glue;
glue overflow holes are formed in the wall of the through hole groove, and are used for exhausting air and redundant glue solution when glue is filled into the through hole groove;
the temperature detection structure comprises a thermistor for monitoring the temperature of the crystal, the thermistor is arranged in a first counter bore, and the first counter bore is arranged at the top of the tube shell;
the performance calibration structure comprises a radioactive source used in on-orbit energy calibration of the crystal, and the radioactive source is arranged on a tube shell or an end cover;
furthermore, the end cover comprises a cover plate and a folded edge, wherein the inner side surface of the cover plate is provided with an installation groove for embedding the radioactive source, and the outer side surface of the cover plate is convex corresponding to the installation groove, so that the thickness of any position of the cover plate is consistent.
Furthermore, the upper end of the head of the pipe shell is provided with a second counter bore with an upward opening, and the radioactive source is arranged in the second counter bore.
Further, the crystal module is used for detecting hard X-rays with the power of 30keV or above, the radioactive source is Ba133, the thickness of the end cover plate is 2mm, the inner diameter of the end cover plate is 31mm, the diameter of the installation groove is 5mm, and the depth of the installation groove is 0.5 mm.
Furthermore, the end cover is connected with the pipe shell through threads, and anti-loosening glue is coated on the connecting part of the end cover and the pipe shell.
Has the advantages that:
1) through structural improvement, the related photoelectric conversion module and the related crystal module are relatively independent, the problem of convenience in replacement of the satellite-borne crystal and the photoelectric conversion module can be solved, the inheritance of aerospace products can be improved, and the development period can be shortened;
2) according to the invention, through structural improvement, the structural quality of the detection device is effectively reduced through a modularized compact integrated design while providing electromagnetic shielding protection required by the photoelectric conversion module;
3) through structural improvement, the problems of satellite-borne crystal module protection (mechanical vibration is extremely strong during satellite launching, the crystal is extremely easy to deliquesce and needs good sealing protection) and photoelectric conversion module protection are solved, so that the detection device can meet the launching environment requirement through examination of a space mechanical environment;
4) in the detection device, the crystal module is designed, so that the on-orbit performance self-calibration function of the detection crystal can be met, the performance of the detection device such as energy resolution and the like can be guaranteed, the on-orbit temperature of the detection crystal can be monitored, the change of the thermal influence of the detector is reduced by utilizing ground temperature calibration (the on-orbit scientific data is subjected to temperature compensation or correction by utilizing ground calibration data), and the deviation of scientific data analysis is reduced;
5) the invention obviously improves the array integration level of the space detector by reasonable design of the installation interface (butt joint hole, counter bore and the like).
Drawings
FIG. 1 is a first perspective view of a crystal module;
FIG. 2 is a second perspective view of a crystal module;
FIG. 3 is a longitudinal cross-sectional view of a crystal module;
FIG. 4 is a schematic structural view of an end cap of a crystal module;
FIG. 5 is a schematic cross-sectional view of the crystal module end cap in the direction D-D;
FIG. 6 is a schematic cross-sectional view of the crystal module envelope in the direction A-A, B-B;
fig. 7 is a structural view of a photoelectric conversion module;
fig. 8 is a longitudinal sectional view of the photoelectric conversion module;
FIG. 9 is an enlarged view of a portion of the structure of FIG. 8;
fig. 10 is a structural view of an outer bushing of the photoelectric conversion module;
fig. 11 is a structural view of an inner liner of the photoelectric conversion module;
fig. 12 is a structural view of a magnetic shield device;
fig. 13 is a structural view of the combination of the photoelectric conversion module and the thermally conductive holder;
fig. 14 is an overall structural view of the photodetecting unit;
fig. 15 is a front view of the photodetecting unit;
FIG. 16 is a sectional view in the A-A direction of the photodetecting unit;
FIG. 17 is a cross-sectional view in the B-B direction of the photodetecting unit;
fig. 18 is a top view of the photodetecting unit.
Detailed Description
In order to clarify the structural design of the present invention, the present invention will be further described with reference to the following detailed description of the preferred embodiments in conjunction with the accompanying drawings. The terms "upper," "lower," "top," "bottom," and the like are used herein for the sake of clarity in describing the temporary orientations used in the structures, and it will be understood by those skilled in the art that the above descriptions will vary depending on the particular reference.
The first embodiment is as follows:
the space-borne space photoelectric conversion module shown in fig. 7 to 13 includes a photoelectric conversion device 205, an electronic readout circuit board 201 (hereinafter referred to as a PCB), a protection structure, and other components.
The photoelectric conversion device 205 is used for converting the flash light emitted by the crystal 109 into photoelectrons, and in this embodiment, a commonly used photomultiplier tube (PMT) is used, and since the PMT is a glass device, the space satellite-borne device needs to experience a very strong mechanical vibration environment, and therefore the space satellite-borne device needs to be protected by the buffer glue 204.
The protective structure further comprises an inner bushing 207, a magnetic shielding device 206, an outer bushing 203 and a buffer rubber 204, wherein the inner bushing 207 and the outer bushing 203 are both made of magnesium-aluminum alloy materials, the magnetic shielding device 206 is a permalloy sheet, and the buffer rubber 204 can be made of silicon rubber with the model number of Sylgard 170 or other similar silicon rubber.
The inner liner 207 is cylindrical, the radial thickness of the main body cylinder wall is 1mm, small flanges 2072 with the height of 0.5mm (the radial height of the liner) are arranged outwards at the top end and the bottom end of the inner liner for installing and positioning the magnetic shielding device 206, the magnetic shielding device 206 is wrapped outside the inner liner 207, and the top and the bottom of the magnetic shielding device are respectively abutted to the small flanges 2072 at the top end and the bottom end of the inner liner 207.
The magnetic shield 206 is made of a single layer of permalloy foil 0.027mm thick and is designed to wrap three turns around the inner sleeve 207 in this embodiment. Photoelectric conversion device receives external magnetic field's influence easily, consequently increases magnetic shield 206, in order to fix a position magnetic shield, in the meticulous compactification design of inside bush and outside bush of this embodiment magnalium preparation, owing to adopted metal construction, magnetic shield 206 can contact with inside bush 207 to avoid magnetic shield 206 to form isolated conductor in the space, prevent that it from causing the damage to photoelectric conversion device.
The long through hole grooves which are uniformly distributed are formed in the side wall of the inner bushing 207, so that the buffer glue poured into the inner bushing 207 seeps out through the through hole grooves and contacts with the magnetic shielding device 206, the contact friction force of the magnetic shielding device 206 is improved, and the magnetic shielding device 206 is prevented from rotating inside.
The outer bushing 203 comprises a sleeve and bracket connection structure:
an inner sleeve 207 wrapping a magnetic shielding device 206 is arranged in a sleeve of the outer sleeve 203, the upper edge of the opening of the sleeve of the outer sleeve 203 is higher than the upper edge of the opening of the inner sleeve 207, and gaps between the photoelectric conversion device 205 and the side walls of the inner sleeve 207 and the outer sleeve 203 are filled by buffer glue 204;
the support connecting structure comprises a first flange arranged at the bottom of the sleeve, a second flange arranged in the middle or at the upper part of the sleeve and a mounting support fixed on the second flange, the mounting support is of a frame type structure, and the PCB 201 is fixed at the top end of the mounting support and is electrically connected with the photoelectric conversion device 205 below the PCB.
The outer contour of the first flange is rectangular, the length and width of the first flange are larger than the outer diameter of the small bottom end flanging of the inner liner 207, during assembly, the upper surface of the small bottom end flanging of the inner liner 207 abuts against the lower surface of the first flange, namely the design of the small bottom end flanging is used for installation and positioning of the inner liner 207, the first flange is simultaneously provided with a first butt hole 2022 for connecting a crystal module, and the first butt hole 2022 is located on the periphery of the small bottom end flanging in the radial direction.
At a position corresponding to the first mating hole 2022, the top of the crystal module case 101 is provided with a female-type screw connection hole 1051, i.e., a third mating hole. The second flange is provided with a reserved through hole 2022-1 for a screwdriver to pass through, so that a tool can vertically extend into the reserved through hole 2022-1 when an operator screws a lower screw (the screw installed in the crystal module threaded hole 1051), and the screw screwing is more convenient.
The mounting bracket comprises four upright posts which are arranged in a rectangular shape, wherein three adjacent upright posts are connected through a cross beam, as shown in fig. 10, the upright posts and the cross beam are provided with 7 threaded holes 2023 for mounting the PCB, wherein three upright posts are pre-mounted, and the rest 4 upright posts can be used for further fastening the PCB or serving as external interfaces, such as wiring and the like, according to the needs.
A heat conducting support 3 is arranged above the PCB, as shown in the photoelectric detection unit array shown in fig. 13, the heat conducting support 3 is arranged at a position between two adjacent photoelectric detection units, and extends longitudinally, while the heat conducting support 3 contacts with the edge parts of the left and right PCB, the boss flange 2034 corresponding to the edge part also contacts, and the boss flange 2034 has the same height as the upper surface of the initially positioned PCB. The contact area between the photoelectric detection unit and the heat conduction bracket 3 can be increased through the boss flange 2034, and the heat conduction efficiency can be improved. The flanging area can be determined according to the heat condition, specifically, in the embodiment, the flanging width of the bosses on the left side and the right side which are in contact with the heat conduction support 3 is 2mm, the flanging width of the bosses on the other side is 4mm, and the length is 22 mm.
The photoelectric conversion module 2 is further provided with a temperature sensor for monitoring temperature, and the temperature sensor is mounted on the boss flange 2034 of the PCB and the heat conducting bracket, which are not in contact with each other, or mounted on the first flange. When the temperature sensor is mounted on the boss flange 2034, the temperature sensor is fixed in the temperature sensor mounting hole 2031 on the boss flange 2034, and the sensor and the cable are both fixed by silicon rubber; when the temperature sensor is mounted on the first flange, the temperature sensor is fixed in the temperature sensor mounting hole 2033 on the first flange, and the second flange is provided with a threading hole 2032 at a position corresponding to the temperature sensor mounting hole 2033. The temperature sensor is arranged to measure the temperature of the photoelectric conversion module after the on-track thermal balance is achieved, and then the on-track gain of the photoelectric tube is subjected to temperature compensation and correction by using the result of calibrating the temperature of the photoelectric conversion module. The two installation modes can be selected simultaneously or alternatively according to requirements.
The basic outline of the second flange is also rectangular, a second butt joint hole 2021 for connecting an external complete machine is arranged at the edge of the second flange, and the second butt joint hole 2021 is positioned at the periphery of the first flange in the radial direction to prevent the two from generating interference when in butt joint.
According to experimental comparison, compared with the aluminum alloy structure of the past module, the photoelectric conversion module of the embodiment has the structural quality reduced by about 33% on the premise of meeting the structural strength.
Example two:
a space-borne space photoelectric detection device comprises a photoelectric detection unit array and a heat conduction support 3. As shown in fig. 14 to 18, the photodetection unit is formed by butting the crystal module 1 and the photoelectric conversion module 2, and the structural design of the photoelectric conversion module 2 is the same as that of the first embodiment.
The structure of the crystal module 1, as shown in fig. 1 to 5, includes a crystal 109, a crystal protection structure, a temperature detection structure, a performance calibration structure, and an installation interface.
The crystal protection structure comprises a tube shell 101, an end cap 103 and a quartz glass plate 106, wherein the tube shell 101 and the end cap 103 are made of aluminum material in the embodiment, and in order to further reduce the structural quality, magnesium alloy can be considered.
The shape of the pipe shell 101 is T-shaped, the upper part is a head part which is rectangular block-shaped, the lower part is a cylindrical pipe body, and the head part and the pipe body are integrally formed. A cylindrical body housing is provided in the center of housing 101, and crystal 109 is mounted in the body housing.
The end cap 103 is composed of an integrally formed cover plate and an annular flange, as shown in fig. 5. The inner side of the annular folded edge is provided with an internal thread, and the end cover 103 is sleeved at the bottom end of the tube shell 101 and is fixedly connected with the tube shell 101 through a thread structure to block a bottom port of the main body shell cavity. During the fastening of cap 103 to housing 101, an anti-loosening glue is applied for preventing loosening, and for sealing to prevent water vapor from penetrating and deliquescing the crystal.
The top of the tube shell 101 is provided with a through hole groove for glue filling (optical coupling glue filling, and also used as buffer glue) and an annular flange protruding inwards, the annular flange is positioned between the through hole groove and the main body shell cavity, the diameter of the through hole groove is larger than that of the main body shell cavity, and the diameter of the main body shell cavity is larger than that of the central through hole of the annular flange, so that a variable stepped tube cavity structure is formed between the main body tube cavity of the tube shell 101 and the top surface of the tube shell 101.
A quartz glass plate 106 is placed on top of the crystal 109, blocking the top port of the body shell cavity, or central hole of the annular flange. The lower surface of the quartz glass sheet 106 is tightly attached to the top surface of the crystal 109, and the edge of the upper surface is fixedly sealed with the lower surface of the annular flange through silica gel. The gap between crystal 109 and the sidewall of package 101 and end cap 103 is then filled with an optical coupling glue.
The height of the through hole groove is 2mm, the groove wall of the through hole groove is provided with a glue overflow hole 102, and when glue is poured into the through hole groove, the glue overflow hole 102 is used for exhausting air and redundant glue. The optical coupling glue is also used as buffer glue for carrying out buffer protection on devices such as quartz glass and the like.
The temperature detection structure comprises a thermistor for monitoring the temperature of the crystal 103, the thermistor is arranged in a first counter bore 104, the first counter bore 104 is arranged at the top of the tube shell 101 and is designed to be phi 2.5mm multiplied by 6mm (depth), an MF61 type thermistor is selected for dispensing and fixing, and the type of glue is GD 414-C. In the test process of the ground, the thermistor is used for measuring the response of the crystal at different temperatures, and the relation of the response of the crystal along with the change of the temperature can be obtained. Therefore, after the track, as long as the temperature of the crystal can be measured, temperature compensation and correction, so-called temperature calibration, can be performed.
The performance scaling structure includes a radioactive source for use in on-orbit energy scaling of crystals, which is mounted on the envelope 101 or end cap 103.
The inner side surface of the cover plate of the end cover 103 is provided with a mounting groove 072 capable of being embedded with a radioactive source, the outer side surface of the cover plate is convex corresponding to the position of the mounting groove 072, so that the thickness of any position of the cover plate in the axial direction is consistent, namely when the mounting groove 072 is a cylindrical groove, the outside is reflected as a cylindrical boss.
The top of the housing 101 is provided with a second counterbore 1071 (the end opposite the first counterbore 104) in which the radiation source is mounted. The second counter bore 1071 is an M4 threaded hole with the depth of 6mm, the second counter bore can be screwed by screws after installation, and the radioactive source needs to be subjected to dispensing treatment before screwing.
The radioactive source is used for ground and on-orbit performance calibration, specifically, in the embodiment, as the target detects hard X-rays above 30keV, the thickness of the cover plate of the end cover 103 is designed to be 2mm, and the inner diameter is 31 mm; the diameter of the mounting groove 072 is 5mm, the depth is 0.5mm, and Ba133 is selected by using a radioactive source (exemption, namely, the activity of the radioactive source is below class V). The thickness of the end cover plate can be adjusted according to actual needs, and the thickness variation range is 0.5 mm-3.0 mm.
In order to realize linear calibration and absolute energy calibration of detector energy, a method of calibrating a source by using a radioactive isotope is generally used on the ground. The design provides an interface of a radioactive source (exemption source Ba 133), and can provide a plurality of X-ray characteristic peaks such as 32KeV, 81KeV, 356KeV and the like in a detection energy range by placing the Ba133 source, so that the functions of on-orbit energy linear calibration and absolute energy calibration of the detector are realized.
The mounting position of the radioactive source can be selected alternatively, and the radioactive source has advantages and disadvantages: the installation of the exempt source on the end cover is safer and closer to the crystal (the closer to the crystal, the purer the X-ray obtained by the crystal, and the higher the precision, if the X-ray is far away from the crystal, the X-ray of the radioactive source can penetrate other substances to generate background (namely impurities) to influence the precision); the exemption source installed on the tube shell is positioned outside, and the characteristic X ray of the exemption source needs to penetrate through a shell with a certain thickness, so that a new background can be introduced, but the installation is more convenient.
A scintillation crystal is a crystal that can emit a flash of light by converting the kinetic energy of high-energy particles into light energy when struck by high-energy particles such as X-rays. As the detection target mainly aims at the solar hard X-ray, the crystal 109 selected by the embodiment is a lanthanum bromide crystal with high energy resolution and fast time response, the size is phi 25mm multiplied by 25mm (H), and the optical coupling adhesive adopts RTV 612. Cerium bromide crystals may be selected if they are more sensitive to background and not too high for energy resolution. The crystal can be adaptively replaced according to different detection purposes, and other scintillation crystals of different types such as cesium iodide, sodium iodide and the like can be obtained. Similar to the optical coupling adhesive, RTV615 can be selected.
The mounting interface further includes a threaded connection hole 1051 (third docking hole) disposed at the top end of the head of the case 101, and a threaded connection hole 1052 (fourth docking hole) disposed at the bottom end of the head of the case 101, where the threaded hole 1051 is used for docking with the photoelectric conversion module 2 above, and the threaded hole 1052 is used for docking with an external complete machine below. The threaded holes 1051 and 1052 are both threaded counterbores with the diameter of M3 multiplied by 10mm, anti-loosening glue is needed in the screwing process, and the depth and the size of the threaded holes can be adaptively modified according to different purposes and requirements.
As shown in fig. 13, the heat conducting bracket 3 extends along the longitudinal direction of the photodetecting unit array, and the bottom of the heat conducting bracket is provided with a folded edge for overlapping the left and right photoelectric conversion modules 2. It is worth to be noted that most of the space satellite-borne photoelectric detection units are designed in an array structure (see a dark matter particle detection satellite BGO energy meter and the like), and the reserved boss flange 2034 design enables the adjacent photoelectric detection units to be connected with the heat conduction bracket together, so that the temperature uniformity of the array detection units is improved.
The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the foregoing description only for the purpose of illustrating the principles of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the invention as defined by the appended claims, specification, and equivalents thereof.
Claims (10)
1. The space-borne space photoelectric conversion module is characterized by comprising a photoelectric conversion device (205), an electronic reading circuit board (201) and a protection structure:
the protective structure comprises an inner bushing (207), a magnetic shielding device (206) and an outer bushing (203), wherein the inner bushing (207) and the outer bushing (203) are both made of magnesium-aluminum alloy materials, and the magnetic shielding device (206) is made of permalloy sheets;
the top end and the bottom end of the inner liner (207) are both outwards provided with small flanges (2072) with a certain height for installing and positioning the magnetic shielding device (206), the magnetic shielding device (206) is wrapped on the outer side of the inner liner (207), and the top and the bottom of the magnetic shielding device are respectively abutted against the small flanges (2072) at the upper end and the lower end of the inner liner (207); the side wall of the inner bushing (207) is provided with a through hole groove, so that buffer glue filled into the inner bushing (207) seeps out through the through hole groove and contacts with the magnetic shielding device (206), the contact friction force of the magnetic shielding device (206) is improved, and the magnetic shielding device (206) is prevented from rotating inside;
the outer bushing (203) comprises a sleeve and a bracket connection structure;
an inner bushing (207) wrapped by a magnetic shielding device (206) is arranged in a sleeve of an outer bushing (203), the upper edge of a tube opening of the sleeve of the outer bushing (203) is higher than the upper edge of the tube opening of the inner bushing (207), and gaps among the photoelectric conversion device (205), the inner bushing (207) and the side wall of the outer bushing (203) are filled by buffer glue (204);
the support connecting structure comprises a first flange arranged at the bottom of the sleeve, a second flange arranged in the middle or at the upper part of the sleeve and a mounting support fixed on the second flange, the mounting support is of a frame type structure, and an electronic reading circuit board (201) is fixed at the top end of the mounting support and is electrically connected with a photoelectric conversion device (205) below the mounting support;
the size of the first flange is larger than that of the small bottom flanging of the inner liner (207), when the crystal module assembling device is assembled, the upper surface of the small bottom flanging of the inner liner (207) abuts against the lower surface of the first flange and is used for installing and positioning the inner liner (207), the first flange is simultaneously provided with a first butt hole (2022) for connecting the crystal module, and the first butt hole (2022) is positioned on the periphery of the small bottom flanging in the radial direction;
the second flange is provided with a reserved through hole (2022-1) for a screwdriver to pass through at a position corresponding to the first butt hole (2022).
2. The space-borne space photoelectric conversion module according to claim 1, wherein:
the mounting bracket comprises four upright posts which are arranged in a rectangular shape, wherein three adjacent upright posts are connected through a cross beam, boss flanges (2034) which are bent upwards and inwards are arranged on the cross beam, and the boss flanges (2034) in three directions are used for limiting and blocking the electronic reading circuit board (201) for primary positioning before fixing;
the heat conduction support (3) is arranged above the electronics reading circuit board (201), the electronics reading circuit board (201) after initial positioning is equal in height to the upper surface of the boss flanging (2034), so that the boss flanging (2034) corresponding to the edge part is also contacted while the heat conduction support (3) is contacted with the edge part of the electronics reading circuit board (201), namely, the contact area of the detection unit and the heat conduction support (3) is increased through the boss flanging (2034), and the heat conduction efficiency is improved.
3. The space-borne space photoelectric conversion module according to claim 1, wherein a temperature sensor for monitoring the photoelectric conversion module is arranged, and the temperature sensor is mounted on a boss flange (2034) of the electronic readout circuit board (201) which is not in contact with the heat conducting bracket, or mounted on the first flange;
when the temperature sensor is arranged on the boss flanging (2034), the temperature sensor is fixed in a temperature sensor mounting hole (2031) on the boss flanging (2034);
when the temperature sensor is mounted on the first flange, the temperature sensor is fixed in a temperature sensor mounting hole (2033) on the first flange, and a threading hole (2032) is arranged at the position of the second flange corresponding to the temperature sensor mounting hole (2033).
4. The space-borne space photoelectric conversion module according to claim 1, wherein:
the second flange is provided with a second butt joint hole (2021) connected with an external whole machine, and the second butt joint hole (2021) is positioned on the periphery of the first flange in the radial direction.
5. A space-borne spatial photoelectric conversion module according to claim 1, wherein the permalloy flakes have a thickness of 0.027mm and are wrapped three times around an inner liner (207).
6. A space-borne space photodetection device comprising an array of a plurality of photodetection units, said photodetection units being comprised of a crystal module (1) and a photoelectric conversion module (2) according to any of claims 1-5, said crystal module (1) comprising a crystal (109), a crystal protection structure, a temperature detection structure and a performance scaling structure;
the crystal protection structure comprises a tube shell (101), an end cover (103) and a quartz glass sheet (106) for sealing;
the crystal shell is characterized in that the tube shell (101) is T-shaped and comprises a rectangular block-shaped head and a cylindrical lower tube body which are integrally formed, a cylindrical main body shell cavity is formed in the center of the tube shell, the crystal (103) is installed in the main body shell cavity, and an end cover (103) is sleeved at the bottom end of the tube shell (101) and is hermetically connected with the tube shell (101) to block a bottom port of the main body shell cavity;
a third butt joint hole (1051) with an upward opening is formed in the upper end of the head of the tube shell (101) corresponding to the position of the first butt joint hole (2022) of the photoelectric detection module, and the third butt joint hole is matched with the first butt joint hole (2022) for use in butt joint of the crystal module (1) and the photoelectric detection module (2) to fasten the connection of the crystal module (1) and the photoelectric detection module (2); the lower end of the head of the pipe shell (101) is provided with a fourth butt joint hole (1051) with a downward opening, the fourth butt joint hole (1051) is used for being connected with an external complete machine, and the third butt joint hole (1051) and the fourth butt joint hole (1052) are both designed into counter bores;
the top surface of the head of the pipe shell (101) is provided with a through hole groove for glue filling and an annular flange protruding inwards, the annular flange is positioned between the through hole groove and the main body shell cavity, the diameter of the through hole groove is larger than that of the main body shell cavity, and the diameter of the main body shell cavity is larger than that of a central through hole of the annular flange;
the quartz glass sheet (106) is arranged at the top end of the crystal (109), the lower surface of the quartz glass sheet is attached to the top surface of the crystal (109), the edge part of the upper surface is hermetically connected with the lower surface of the annular flange to block the top port of the main body shell cavity, and a gap between the crystal (109) and the shell (101) and the end cover (103) is filled with optical coupling glue;
glue overflow holes (102) are formed in the wall of the through hole groove, and when glue is filled into the through hole groove, the glue overflow holes (102) are used for discharging air and redundant glue;
the temperature detection structure comprises a thermistor for monitoring the temperature of the crystal (103), the thermistor is arranged in a first counter bore (104), and the first counter bore (104) is arranged at the top of the tube shell (101);
the performance scaling structure includes a radioactive source for use in on-orbit energy scaling of crystals, the radioactive source being mounted on an enclosure (101) or end cap (103).
7. The space-borne space photoelectric detection device according to claim 6, wherein the end cap (103) comprises a cover plate and a folded edge, the inner side surface of the cover plate is provided with a mounting groove (072) for embedding the radioactive source, and the outer side surface of the cover plate is convex corresponding to the position of the mounting groove (072), so that the thickness of the cover plate at any position is consistent.
8. A space-borne space photodetection device according to claim 6, characterized in that the upper end of the head of the package (101) is provided with a second counter bore (1071) opening upwards, the radioactive source being mounted in said second counter bore (1071).
9. The spaceborne space photoelectric detection device according to claim 7, wherein the radiation source is Ba133, the thickness of the cover plate of the end cover (103) is 2mm, the inner diameter of the cover plate is 31mm, the diameter of the mounting groove (072) is 5mm, and the depth of the mounting groove is 0.5 mm.
10. A space-borne space photoelectric detection device according to claim 6, wherein the end cap (103) is connected with the tube shell (101) through threads, and the connection part of the end cap and the tube shell is coated with anti-loosening glue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010212141.5A CN111522047B (en) | 2020-03-24 | 2020-03-24 | Space-borne space photoelectric conversion module and photoelectric detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010212141.5A CN111522047B (en) | 2020-03-24 | 2020-03-24 | Space-borne space photoelectric conversion module and photoelectric detection device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111522047A true CN111522047A (en) | 2020-08-11 |
| CN111522047B CN111522047B (en) | 2022-01-25 |
Family
ID=71901043
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010212141.5A Active CN111522047B (en) | 2020-03-24 | 2020-03-24 | Space-borne space photoelectric conversion module and photoelectric detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111522047B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004112083A1 (en) * | 2003-06-11 | 2004-12-23 | Hamamatsu Photonics K.K. | Multi anode-type photoelectron intensifier tube and radiation detector |
| WO2007098493A2 (en) * | 2006-02-22 | 2007-08-30 | The Regents Of The University Of California | Large-area flat-panel photon detector with hemispherical pixels and full area coverage |
| US20070205371A1 (en) * | 2006-03-02 | 2007-09-06 | Canon Kabushiki Kaisha | Radiation detecting apparatus, scintillator panel, radiation detecting system, and method for producing scintillator layer |
| CN101424742A (en) * | 2008-10-07 | 2009-05-06 | 中国科学院紫金山天文台 | Method for detecting dark matter by utilizing latex chamber detector |
| US20110276526A1 (en) * | 2008-12-19 | 2011-11-10 | Europhoton Gmbh, Gesellschaft Fur Optische Sensori | position resolved measurement apparatus and a method for acquiring space coordinates of a quantum beam incident thereon |
| CN104849745A (en) * | 2015-06-02 | 2015-08-19 | 中国科学院紫金山天文台 | Protection structure of satellite-borne space crystal array detector |
-
2020
- 2020-03-24 CN CN202010212141.5A patent/CN111522047B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2004112083A1 (en) * | 2003-06-11 | 2004-12-23 | Hamamatsu Photonics K.K. | Multi anode-type photoelectron intensifier tube and radiation detector |
| WO2007098493A2 (en) * | 2006-02-22 | 2007-08-30 | The Regents Of The University Of California | Large-area flat-panel photon detector with hemispherical pixels and full area coverage |
| US20070205371A1 (en) * | 2006-03-02 | 2007-09-06 | Canon Kabushiki Kaisha | Radiation detecting apparatus, scintillator panel, radiation detecting system, and method for producing scintillator layer |
| CN101424742A (en) * | 2008-10-07 | 2009-05-06 | 中国科学院紫金山天文台 | Method for detecting dark matter by utilizing latex chamber detector |
| US20110276526A1 (en) * | 2008-12-19 | 2011-11-10 | Europhoton Gmbh, Gesellschaft Fur Optische Sensori | position resolved measurement apparatus and a method for acquiring space coordinates of a quantum beam incident thereon |
| CN104849745A (en) * | 2015-06-02 | 2015-08-19 | 中国科学院紫金山天文台 | Protection structure of satellite-borne space crystal array detector |
Non-Patent Citations (3)
| Title |
|---|
| 张双南: "中国空间站的高能宇宙辐射探测设施", 《国际太空》 * |
| 张岩: "空间太阳硬X射线成像仪量能器读出电子学设计", 《天文学报》 * |
| 郭建华: "暗物质空间探测器BGO量能器的读出设计", 《天文学报》 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111522047B (en) | 2022-01-25 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| Produit et al. | Design and construction of the POLAR detector | |
| KR101001428B1 (en) | X-ray tube and x-ray source | |
| CA2483559A1 (en) | Instrumentation package and integrated radiation detector | |
| GB2259433A (en) | Scintillation camera plate assembly | |
| CN111522047B (en) | Space-borne space photoelectric conversion module and photoelectric detection device | |
| KR20210076085A (en) | radiation imaging device | |
| CN111474570B (en) | Crystal module and satellite-borne space photoelectric detection unit comprising same | |
| Xu et al. | The design and performance of charged particle detector onboard the GECAM mission | |
| US10458834B2 (en) | Radiation detector | |
| JPH0565833B2 (en) | ||
| JP2012088152A (en) | Radiation detection device | |
| CN109581467B (en) | Gamma ray detector | |
| Vasiliev et al. | Module for thermal neutrons registration based on uncooled silicon detectors and metal gadolinium converter | |
| KR20080089340A (en) | A molten steel level measuring device with a long scintillator | |
| US20050190883A1 (en) | X-ray source | |
| JP4952729B2 (en) | Neutron detector structure | |
| Held et al. | Construction of the Forward Endcap Calorimeter of the PANDA Experiment at FAIR | |
| US4336458A (en) | Diagnostic radiology apparatus for producing layer images of an examination subject | |
| KR20210076091A (en) | A radiation imaging device, a manufacturing method of the radiation imaging device, and a repair method of the radiation imaging device | |
| EP0535634B1 (en) | Radiation detector and its manufacturing method | |
| CN117214940A (en) | Scintillation crystal radiation detector | |
| KR102409462B1 (en) | Bias gamma-ray detector for irradiation test | |
| CN216670287U (en) | Novel anti-recovery detector device | |
| CN114270470A (en) | Electronic detector | |
| Lund et al. | Jem-X the X-Ray Monitor on Integral |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |