CN108801169B - One-dimensional PSD sensor assembly suitable for satellite structure in-orbit deformation measurement - Google Patents
One-dimensional PSD sensor assembly suitable for satellite structure in-orbit deformation measurement Download PDFInfo
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- CN108801169B CN108801169B CN201810664429.9A CN201810664429A CN108801169B CN 108801169 B CN108801169 B CN 108801169B CN 201810664429 A CN201810664429 A CN 201810664429A CN 108801169 B CN108801169 B CN 108801169B
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- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
- G01B11/16—Measuring arrangements characterised by the use of optical techniques for measuring the deformation in a solid, e.g. optical strain gauge
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Abstract
The invention provides a one-dimensional PSD sensor component suitable for satellite structure on-orbit deformation measurement, which comprises a shell and a PSD signal processing board arranged in the shell, wherein a PSD signal processing circuit is arranged on the PSD signal processing board and comprises a one-dimensional PSD chip, a current sampling circuit, a voltage amplifying circuit, an output protection circuit, a precise power circuit, a heating circuit and a temperature measuring circuit, and the one-dimensional PSD chip is used for sensing the position of an incident laser spot; the current sampling circuit and the precise power supply circuit are connected with the one-dimensional PSD chip; the voltage amplifying circuit is connected with the current sampling circuit and the output protection circuit, and the heating circuit is connected with external power supply; and the temperature measuring circuit is connected with an external temperature acquisition single machine. The method can be used for realizing the non-contact measurement of the on-orbit deformation of the satellite structure; the device has the functions of self temperature measurement and automatic thermal control in low-temperature environment.
Description
Technical Field
The invention relates to the field of spacecrafts, in particular to a one-dimensional PSD sensor assembly suitable for satellite structure in-orbit deformation measurement.
Background
Due to the complexity of the satellite structure and the material thereof, the repeated and alternate change of the space thermal environment is serious, which may cause the obvious thermal deformation of the satellite structure, and the structural deformation may cause serious influence on the precision of partial load imaging and pointing on the satellite. Along with the improvement of the performance of the spacecraft, the influence of the structural deformation on the performance index of the main load of the in-orbit satellite is more and more emphasized, the application requirement of the structural deformation measurement technology is increasingly shown and important, and data support is provided for structural deformation inhibition and in-orbit correction through structural deformation in-orbit monitoring. Most of traditional structural deformation measurement is based on contact type measuring devices such as optical fibers, the size and the weight are generally large, and particularly when the device is applied to a long distance and a large array surface, the contact type measuring device occupies more whole star size, weight and thermal control resources and is easy to influence measured objects, so that the development of a light-weight and non-contact type measuring device is more significant.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a lightweight and autonomous thermal control non-contact satellite structure in-orbit deformation measuring device in a low-temperature environment, which is particularly suitable for the in-orbit deformation measurement of a satellite structure with a long distance and a large array surface.
In order to solve the technical problems, the invention is specifically realized by the following technical scheme:
the one-dimensional PSD sensor assembly suitable for satellite structure on-orbit deformation measurement comprises a shell and a PSD signal processing board arranged in the shell, wherein a PSD signal processing circuit is arranged on the PSD signal processing board and comprises a one-dimensional PSD chip, a current sampling circuit, a voltage amplifying circuit, an output protection circuit, a precise power circuit, a heating circuit and a temperature measuring circuit, and the one-dimensional PSD chip is used for sensing the position of an incident laser spot; the current sampling circuit and the precise power supply circuit are connected with the one-dimensional PSD chip; the voltage amplifying circuit is connected with the current sampling circuit and the output protection circuit, and the heating circuit is connected with external power supply; and the temperature measuring circuit is connected with an external temperature acquisition single machine.
Preferably, the housing includes an optical filter, a front housing, a rear cover and screws, the housing is fixed to the tested structure interface through the screws and mounting holes on the front housing, the optical filter is mounted at a PSD light-passing hole of the front housing, and an incident laser beam passes through the optical filter and then strikes the one-dimensional PSD chip.
Preferably, the PSD signal processing board is of a single board structure, the one-dimensional PSD chip is mounted on the front surface of the PSD signal processing board, and the PSD signal processing board is aligned to the PSD light-passing hole on the front shell when mounted.
Preferably, an electrical connector is welded on the back of the PSD signal processing board and is connected with the outside through the electrical connector, and the electrical connector extends out of the shell through an opening on the rear cover.
Compared with the prior art, the invention has the following beneficial effects:
the method can be used for realizing the non-contact measurement of the on-orbit deformation of the satellite structure, and is particularly suitable for the on-orbit deformation measurement of the satellite structure with a long distance and a large array surface;
secondly, the temperature measuring function is achieved;
thirdly, the system has the function of autonomous thermal control in a low-temperature environment and can be suitable for the environment in or out of a satellite cabin;
the heating circuit can select a positive power supply or a negative power supply to supply power, so that the problem of unbalance of positive and negative power supply power when a plurality of one-dimensional PSD sensor assemblies are used simultaneously is avoided;
fifthly, the output voltage has an amplitude limiting protection function, and the satellite signal acquisition unit is prevented from being damaged by the output high voltage;
sixthly, the shell is made of carbon fiber materials, so that the weight is light, the thermal deformation is small, and the introduced error is greatly reduced;
designing an optical filter on an incident light path, so that an interference light source can be effectively filtered;
eighthly, the single component can realize the function of measuring the structural deformation displacement, a plurality of components can be used simultaneously, and the function of measuring the flatness deformation and the plane pointing deformation can be realized through reasonable layout.
Drawings
Other characteristic objects and advantages of the invention will become more apparent upon reading the detailed description of non-limiting embodiments with reference to the following figures.
FIG. 1 is a schematic view of a housing of the present invention;
FIG. 2 is a schematic diagram of a PSD signal processing circuit according to the present invention;
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications can be made by persons skilled in the art without departing from the spirit of the invention. All falling within the scope of the present invention.
As shown in fig. 1-2, an embodiment of the present invention provides a one-dimensional PSD sensor assembly suitable for satellite structure in-orbit deformation measurement, including a housing and a PSD signal processing board disposed in the housing, where a mounting base 6 is disposed on a lower bottom surface of the housing, a mounting hole 7 is disposed on the mounting base 6, a PSD signal processing circuit is disposed on the PSD signal processing board, the PSD signal processing circuit includes a one-dimensional PSD chip, a current sampling circuit, a voltage amplifying circuit, an output protection circuit, a precision power supply circuit, a heating circuit, and a temperature measuring circuit, and the one-dimensional PSD chip is used for sensing an incident laser spot position; the current sampling circuit and the precise power supply circuit are connected with the one-dimensional PSD chip; the voltage amplifying circuit is connected with the current sampling circuit and the output protection circuit, and the heating circuit is connected with external power supply; the temperature measuring circuit is connected with an external temperature acquisition single machine; the temperature measuring function of the one-dimensional PSD sensor assembly in a space environment can be realized through a temperature measuring circuit in the PSD signal processing circuit; under the low temperature environment outside the cabin, the heating circuit in the PSD signal processing circuit can be used for realizing the autonomous thermal control under the low temperature environment without occupying the whole satellite thermal control resource.
The shell comprises an optical filter 3, a front shell 1, a rear cover 4 and a screw 5; the back of the PSD signal processing board is welded with an electric connector and is connected with the outside through the electric connector, and the electric connector extends out of the shell through an opening on the rear cover; the optical filter 3 is arranged at the PSD light-passing hole 2 of the front shell, the one-dimensional PSD chip is arranged on the front surface of the PSD signal processing board, the PSD signal processing board is aligned to the PSD light-passing hole on the front shell when being arranged, and an incident laser beam passes through the optical filter and then strikes the one-dimensional PSD chip; the shell is fixed on a tested structure interface through a screw and a mounting hole on the front shell; when the laser device is used, the laser device is arranged at a position with good structural rigidity and small on-orbit deformation of the satellite. The shell is made of carbon fiber materials, so that the light weight of the one-dimensional PSD sensor component is realized, the size is only 20mm multiplied by 10mm multiplied by 30mm, the weight is only 25g, the in-orbit thermal deformation of the one-dimensional PSD sensor component is reduced, and the large measurement error introduced by a measurement system is avoided.
The one-dimensional PSD sensor component suitable for satellite structure in-orbit deformation measurement can be used singly to realize the function of measuring the structural deformation displacement, and a plurality of one-dimensional PSD sensor components can be used simultaneously to realize the functions of measuring the planeness deformation and the plane pointing deformation through reasonable layout; the heating circuit in the PSD signal processing circuit can select a positive power supply or a negative power supply to supply power, so that the problem of unbalance of positive and negative power supply power of a satellite power supply single machine when a plurality of one-dimensional PSD sensor assemblies are used simultaneously is avoided; an output protection circuit in the PSD signal processing circuit has an amplitude limiting protection function, and the satellite signal acquisition single machine is prevented from being damaged by output high voltage.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes and modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention.
Claims (1)
1. One-dimensional PSD sensor subassembly suitable for satellite structure is out of shape in orbit and is measured, its characterized in that: the PSD signal processing circuit comprises a one-dimensional PSD chip, a current sampling circuit, a voltage amplifying circuit, an output protection circuit, a precise power circuit, a heating circuit and a temperature measuring circuit;
the one-dimensional PSD chip is used for sensing the position of an incident laser spot;
the current sampling circuit and the precise power supply circuit are connected with the one-dimensional PSD chip;
the voltage amplifying circuit is connected with the current sampling circuit and the output protection circuit, and the heating circuit is connected with external power supply;
the temperature measuring circuit is connected with an external temperature acquisition single machine;
the shell comprises an optical filter, a front shell, a rear cover and a screw, the shell is fixed on a structure interface to be detected through the screw and a mounting hole on the front shell, the optical filter is mounted at a PSD light through hole of the front shell, and an incident laser beam passes through the optical filter and then strikes the one-dimensional PSD chip;
the PSD signal processing board is of a single-board structure, the one-dimensional PSD chip is installed on the front surface of the PSD signal processing board, and the PSD signal processing board is aligned to a PSD light through hole in the front shell when installed;
the back of the PSD signal processing board is welded with an electric connector and is connected with the outside through the electric connector, and the electric connector extends out of the shell through an opening on the rear cover;
the one-dimensional PSD sensor assembly can realize the non-contact measurement of the on-orbit deformation of a satellite structure, has the self temperature measurement function and the autonomous thermal control function, and can be suitable for the environment in or out of a satellite cabin;
the shell is made of carbon fiber materials;
when the one-dimensional PSD sensor assembly is used singly, the function of measuring the structural deformation displacement can be realized; when a plurality of one-dimensional PSD sensor assemblies are used simultaneously, the flatness deformation and plane pointing deformation measurement functions can be realized through reasonable layout;
the heating circuit in the PSD signal processing circuit can select a positive power supply or a negative power supply to supply power, so that the positive and negative power supply power unbalance of a satellite power supply single machine when a plurality of one-dimensional PSD sensor assemblies are used simultaneously is avoided;
an output protection circuit in the PSD signal processing circuit has an amplitude limiting protection function, and the satellite signal acquisition single machine is prevented from being damaged by output high voltage.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810664429.9A CN108801169B (en) | 2018-06-25 | 2018-06-25 | One-dimensional PSD sensor assembly suitable for satellite structure in-orbit deformation measurement |
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| CN108801169B true CN108801169B (en) | 2020-10-09 |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110017768A (en) * | 2019-03-05 | 2019-07-16 | 上海卫星工程研究所 | A kind of design method avoiding PSD signal processing circuit output negative pressure |
| CN114136229B (en) * | 2021-12-01 | 2023-09-19 | 上海市计量测试技术研究院 | Design method for one-dimensional PSD sensor range splicing |
| CN114485447B (en) * | 2022-01-17 | 2024-01-09 | 上海卫星工程研究所 | Satellite-borne laser measuring device |
| CN114543668B (en) * | 2022-01-24 | 2023-11-10 | 上海卫星工程研究所 | Measuring system and method suitable for ultra-large array plane pointing change |
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| CN106839992A (en) * | 2015-12-03 | 2017-06-13 | 中国科学院光电研究院 | A kind of laser micro-displacement detection means based on PSD |
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| US5790255A (en) * | 1997-02-10 | 1998-08-04 | Xerox Corporation | Transparent light beam detectors |
| CN102620756A (en) * | 2012-03-27 | 2012-08-01 | 天津大学 | Phase sensitive demodulator (PSD) signal single-channel processing method based on modulated laser, and processing circuit |
| CN105526879A (en) * | 2015-11-30 | 2016-04-27 | 上海卫星工程研究所 | In-orbit measuring system and method for deformation of satellite large-array-plane antenna based on fiber grating |
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