Linear array infrared earth sensor

Abstract

The invention relates to the technical field of photoelectric attitude sensors, and discloses a linear array infrared earth sensor which comprises a control unit, a shell and a power supply unit arranged in the shell, the shell is provided with four earth boundary infrared radiation detection units used for receiving infrared radiation from different parts of the earth respectively, and the control unit is connected with the power supply unit. A front-end optical signal conversion electric signal amplification unit for converting an optical signal detected by the earth boundary infrared radiation detection unit into an electric signal and a rear-end electric signal information processing unit for carrying out attitude and calculation on the electric signal are also arranged in the shell; the sensor track is high in universality and wide in detection range.

Description

Technical Field

[0001] The invention belongs to the technical field of photoelectric attitude sensors, and in particular relates to a linear array infrared earth sensor. Background Art

[0002] Infrared earth sensors are sensors that use the earth's own infrared radiation to measure the attitude of a spacecraft relative to the local vertical or local ground position. Currently, there are three main types of infrared earth sensors: horizon-crossing, boundary-tracking, and radiation-heat balance.

[0003] However, most of the existing infrared earth sensors have defects such as weak sensor track versatility and small detection range. Therefore, in view of the above situation, it is urgent to provide a linear array infrared earth sensor to overcome the shortcomings in current practical applications. Summary of the invention

[0004] In view of the above situation, in order to overcome the defects of the prior art, the present invention provides a linear array infrared earth sensor, which effectively solves the problems in the above background technology.

[0005] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a linear array infrared earth sensor, comprising: earth boundary infrared radiation detection units, four groups of which are arranged on a shell, with detection surfaces facing outside the shell, for respectively receiving infrared radiation from different directions of the universe; front-end optical signal conversion electrical signal amplification units, four groups of which are arranged inside the shell, for converting optical signals detected by the earth boundary infrared radiation detection units into electrical signals; and a back-end electrical signal information processing unit, which is arranged inside the shell, for performing information processing on the electrical signals and extracting the earth boundary infrared radiation.

[0006] Preferably, the earth boundary infrared radiation detection unit comprises: a first lens, a spacer ring, a second lens, a first pressure ring, a second pressure ring and a lens barrel arranged on the housing.

[0007] Preferably, the first lens, the spacer ring and the second lens are fixed in the lens barrel by a first pressing ring and a second pressing ring.

[0008] Preferably, the earth boundary infrared radiation detection unit can measure the space vehicle attitude in the range of -16° to 16°.

[0009] Preferably, the linear array infrared earth sensor further comprises: a control unit, which is used to supply power to the power supply unit of the linear array infrared earth sensor via a cable, and convert the power supply unit into the working voltage required by the linear array infrared earth sensor.

[0010] Preferably, the front-end optical signal conversion electrical signal amplification unit comprises:

[0011] Shielding box, used for electrical signal shielding;

[0012] Front-end board, used for front-end electrical signal amplification;

[0013] The detector is an infrared signal sensor used to convert the detected infrared signals from the universe into electrical signals;

[0014] Detector pressure strip, used to fix the detector;

[0015] Detector installation box, used to install and fix the detector;

[0016] The filter is made of germanium material and is used for spectral filtering;

[0017] A filter pressing plate, used for fixing the filter;

[0018] The shielding box is arranged at the bottom of the earth boundary infrared radiation detection unit, the detector installation box is arranged in the shielding box, and the filter, the front end plate and the detector are all arranged in the detector installation box.

[0019] Preferably, the shielding box is fastened to the bottom of the earth boundary infrared radiation detection unit by screws.

[0020] Preferably, the front end plate and the detector are fastened in the detector mounting box by means of detector pressure strips and screws.

[0021] Preferably, the filter is fixed in the detector mounting box by means of a filter pressing plate and screws.

[0022] Compared with the prior art, the beneficial effects of the present invention are as follows: the power supply unit of the earth sensor is powered by the control unit and converted into the required voltage by the power supply unit; the four earth boundary infrared radiation detection units respectively receive infrared radiation from different parts of the earth, and the different infrared radiation energies received by each detection unit are solved through the front-end optical signal conversion electrical signal amplification unit and the back-end electrical signal information processing unit to obtain the attitude of the spacecraft. When the radiation energies received by all the earth boundary infrared radiation detection units are equal after the solution, it indicates that the attitude angle of the spacecraft is zero, otherwise it indicates that the spacecraft has an attitude deviation. The four detection systems constitute a two-dimensional axial deviation. The sensor of the present invention has strong orbit versatility and a wide detection range. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The accompanying drawings are used to provide further understanding of the present invention and constitute a part of the specification. They are used to explain the present invention together with the embodiments of the present invention and do not constitute a limitation of the present invention.

[0024] In the attached picture:

[0025] Figure 1 It is a structural schematic diagram of the present invention.

[0026] Figure 2 It is a schematic diagram of the front cross-sectional structure of the present invention.

[0027] Figure 3 It is a schematic diagram of the structure of the earth boundary infrared radiation detection unit in the present invention.

[0028] Figure 4 It is a schematic diagram of the structure of the front-end optical signal conversion electrical signal amplification unit in the present invention.

[0029] In the figure: 1-earth boundary infrared radiation detection unit, 1-1-lens barrel, 1-2-first lens, 1-3-spacer ring, 1-4-second lens, 1-5-first pressure ring, 1-6-second pressure ring, 1-7-protective cover, 2-front-end optical signal conversion electrical signal amplification unit, 2-1-shielding box, 2-2 front-end plate, 2-3 detector pressure strip, 2-4 detector, 2-5 detector installation box, 2-6 filter, 2-7 filter pressure plate, 3-rear-end electrical signal information processing unit, 4-power supply unit, 5-control unit, 6-housing. DETAILED DESCRIPTION

[0030] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments; based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present invention.

[0031] See also Figure 1-Figure 4 The linear array infrared earth sensor provided by the embodiment of the present invention is an instrument for measuring infrared thermal radiation of the earth. The linear array infrared earth sensor comprises: an earth boundary infrared radiation detection unit 1), four groups of which are arranged on a shell 6, with the detection surface facing the outside of the shell, for respectively receiving infrared radiation from different directions of the universe;

[0032] The front-end optical signal conversion electric signal amplification unit 2 is provided in four groups inside the housing 6, and is used to convert the optical signal detected by the earth boundary infrared radiation detection unit 1 into an electric signal;

[0033] The back-end electrical signal information processing unit 3 is arranged inside the housing 6 and is used to process the electrical signal and extract the infrared radiation of the earth's boundary.

[0034] In an embodiment of the present invention, four earth boundary infrared radiation detection units 1 respectively receive infrared radiation from different parts of the earth, and after the front-end optical signal conversion electrical signal amplification unit 2 and the back-end electrical signal information processing unit 3, the different infrared radiation energies received by each earth boundary infrared radiation detection unit 1 are resolved, thereby obtaining the attitude of the spacecraft. Solve the earth infrared radiation of four attitude angles (roll angle -16°~16°, pitch angle -16°~16°), and the linear array infrared earth sensor obtains the corresponding attitude angle changes through collection, processing and calculation to determine the attitude of the aircraft. The linear array infrared earth sensor is suitable for aircraft orbits of 200-1000km, wherein the earth boundary infrared radiation detection unit 1 applies a band of: 14~16.25μm, can measure the attitude range of spacecraft ±16°, and can measure the attitude accuracy of spacecraft 3σ: 0.05°;

[0035] The earth sensor power supply unit 4 is powered by the control unit 5 and converted into the required voltage by the power supply unit 4; the four earth boundary infrared radiation detection units 1 respectively receive infrared radiation from different parts of the earth, and the different infrared radiation energies received by each detection unit are solved through the front-end optical signal conversion electric signal amplification unit 2 and the back-end electric signal information processing unit 3 to obtain the attitude of the spacecraft. When all the earth boundary infrared radiation detection units 1 receive the same radiation energy after solution, it means that the attitude angle of the spacecraft is zero, otherwise it means that the spacecraft has an attitude deviation. The four detection systems constitute a two-dimensional axial deviation. The sensor track of the present invention has strong versatility and a wide detection range.

[0036] In one embodiment of the present invention, see Figure 3 The earth boundary infrared radiation detection unit 1 comprises a first lens 1-2, a spacer 1-3, a second lens 1-4, a first pressure ring 1-5, a second pressure ring 1-6 and a lens barrel 1-1 arranged on a housing 6, wherein the first lens 1-2, the spacer 1-3 and the second lens 1-4 are pressed and fixed in the lens barrel 1-1 by the first pressure ring 1-5 and the second pressure ring 1-6;

[0037] Exemplarily, the radiation band of the earth's atmosphere is 14 to 16.25 μm, and the detection band of the earth's boundary infrared radiation detection unit 1 is set to 14 to 16.25 μm, thereby capturing the earth's position by detecting the infrared radiation of the earth's atmosphere.

[0038] The earth boundary infrared radiation detection unit 1 can measure the attitude range of spacecraft by -16° to 16°; the attitude angle refers to the pitch angle and roll angle of the spacecraft relative to the local vertical line of the earth when the spacecraft is in orbit.

[0039] The earth boundary infrared radiation detection unit 1 can measure the attitude of a spacecraft with an accuracy of 3σ: 0.05°.

[0040] In this embodiment, the earth boundary infrared radiation enters the infrared detector through the first lens 1-2 and the second lens 1-4 in the earth boundary infrared radiation detection unit 1 to perform infrared radiation imaging. The four earth boundary infrared radiation detection units 1 together constitute the entire infrared earth boundary thermal radiation.

[0041] In one embodiment of the present invention, see Figure 4 The front-end optical signal conversion electrical signal amplification unit 2 includes a shielding box 2-1, a front-end board 2-2, a detector 2-4, a detector pressure strip 2-3, a detector mounting box 2-5, a filter 2-6 and a filter pressure plate 2-7.

[0042] The shielding box 2-1 is used for shielding electrical signals; the front-end board 2-2 is used for amplifying front-end electrical signals;

[0043] The detector 2-4 is an infrared signal sensor, which is used to convert the detected infrared signal of the outer space into an electrical signal; the detector pressure strip 2-3 is used to fix the detector 2-4; the detector mounting box 2-5 is used to install and fix the detector 2-4; the filter 2-6 is made of germanium material and is used for spectral filtering; the filter pressure plate 2-7 is used to fix the filter 2-6.

[0044] The shielding box 2-1 is arranged at the bottom of the earth boundary infrared radiation detection unit 1, the detector mounting box 2-5 is arranged in the shielding box 2-1, and the filter 2-6, the front end plate 2-2 and the detector 2-4 are all arranged in the detector mounting box 2-5.

[0045] Preferably, the shielding box 2-1 is fastened to the bottom of the earth's boundary infrared radiation detection unit 1 by screws, the front end plate 2-2 and the detector 2-4 are fastened to the detector mounting box 2-5 by the detector pressure strip 2-3 and screws, and the filter 2-6 is fixed to the detector mounting box 2-5 by the filter pressure plate 2-7 and screws.

[0046] In this embodiment, the front-end optical signal conversion electrical signal amplification unit 2 converts the optical signal detected by the earth boundary infrared radiation detection unit 1 into an electrical signal, and performs attitude and resolution through the back-end electrical signal information processing unit 3.

[0047] Working principle: the earth sensor power supply unit 4 is powered by the control unit 5 and converted into the required voltage by the power supply unit 4; the four earth boundary infrared radiation detection units 1 respectively receive infrared radiation from different parts of the earth, and the different infrared radiation energies received by each detection unit are solved through the front-end optical signal conversion electrical signal amplification unit 2 and the back-end electrical signal information processing unit 3 to obtain the attitude of the spacecraft. When all the earth boundary infrared radiation detection units 1 receive the same radiation energy after solution, it means that the attitude angle of the spacecraft is zero, otherwise it means that the spacecraft has an attitude deviation. The four detection systems constitute a two-dimensional axial deviation.

[0048] It should be noted that, in this article, relational terms such as first and second, etc. are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Moreover, the terms "include", "comprise" or any other variants thereof are intended to cover non-exclusive inclusion, so that a process, method, article or device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or device.

[0049] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A linear array infrared earth sensor, characterized in that: include: Four groups of earth boundary infrared radiation detection units (1) are arranged on a shell (6), with detection surfaces facing outside the shell, and are used to respectively receive infrared radiation from different directions of space in the universe; A front-end optical signal conversion electric signal amplification unit (2), four groups of which are arranged inside the housing (6) and are used to convert the optical signal detected by the earth boundary infrared radiation detection unit (1) into an electric signal; The back-end electrical signal information processing unit (3) is arranged inside the housing (6) and is used to perform information processing on the electrical signal and extract infrared radiation from the earth's boundary.

2. A linear array infrared earth sensor according to claim 1, characterized in that: The earth boundary infrared radiation detection unit (1) comprises: a first lens (1-2), a spacer ring (1-3), a second lens (1-4), a first pressure ring (1-5), a second pressure ring (1-6), and a lens barrel (1-1) arranged on a housing (6); The first lens (1-2), the spacer ring (1-3) and the second lens (1-4) are pressed and fixed in the lens barrel (1-1) by a first pressing ring (1-5) and a second pressing ring (1-6).

3. A linear array infrared earth sensor according to claim 1 or 2, characterized in that: The earth boundary infrared radiation detection unit (1) can measure the attitude of a spacecraft in a range of -16° to 16°.

4. A linear array infrared earth sensor according to claim 1, characterized in that: It also includes a control unit (5) for supplying power to a power supply unit (4) of the linear array infrared earth sensor via a cable, and converting the power supply unit (4) into a working voltage required by the linear array infrared earth sensor.

5. The linear array infrared earth sensor according to claim 1, characterized in that: The front-end optical signal conversion electrical signal amplification unit (2) comprises: A shielding box (2-1), used for shielding electrical signals; A front-end board (2-2), used for amplifying front-end electrical signals; The detector (2-4) is an infrared signal sensor, which is used to convert the detected infrared signal of the cosmic space into an electrical signal; A detector pressure strip (2-3) for fixing the detector (2-4); A detector installation box (2-5) is used to install and fix the detector (2-4); The filter (2-6) is made of germanium material and is used for spectral filtering; A filter pressing plate (2-7), used for fixing the filter (2-6); The shielding box (2-1) is arranged at the bottom of the earth boundary infrared radiation detection unit (1), the detector installation box (2-5) is arranged in the shielding box (2-1), and the filter (2-6), the front end plate (2-2) and the detector (2-4) are all arranged in the detector installation box (2-5).

6. A linear array infrared earth sensor according to claim 5, characterized in that: The shielding box (2-1) is fastened and installed on the bottom of the earth boundary infrared radiation detection unit (1) by means of screws.

7. The linear array infrared earth sensor according to claim 5, characterized in that: The front end plate (2-2) and the detector (2-4) are fastened in the detector installation box (2-5) via a detector pressure strip (2-3) and screws.

8. The linear array infrared earth sensor according to claim 5, characterized in that: The optical filter (2-6) is fixed in the detector installation box (2-5) via an optical filter pressing plate (2-7) and screws.

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