Linear array infrared earth sensor

Abstract

The application 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. Four earth boundary infrared radiation detection units for receiving infrared radiation from different parts of the earth are arranged on the shell. A front-end light signal conversion electric signal amplification unit for converting light signals detected by the earth boundary infrared radiation detection units into electric signals and a rear-end electric signal information processing unit for performing attitude and solving on the electric signals are further arranged in the shell. The sensor has high generality and wide detection range.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of photoelectric attitude sensors, and particularly relates to a linear array infrared earth sensor. BACKGROUND

[0002] The infrared earth sensor is an attitude sensor for measuring the attitude of a space vehicle relative to a local vertical or a local horizontal plane by using the infrared radiation of the earth.

[0003] However, the existing infrared earth sensors have defects such as weak orbit universality and small detection range. Therefore, in view of the above status, it is urgent to provide a linear array infrared earth sensor to overcome the deficiencies in the current actual application. SUMMARY

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

[0005] To achieve the above object, the application provides the following technical scheme: a linear array infrared earth sensor, comprising: an earth boundary infrared radiation detection unit, which is arranged on a shell in four groups, and has a detection surface facing outward, and is used for receiving infrared radiation from different directions of the universe; a front-end optical signal to electrical signal conversion and amplification unit, which is arranged inside the shell in four groups, and is used for converting the optical signal detected by the earth boundary infrared radiation detection unit into an electrical signal; and a rear-end electrical signal information processing unit, which is arranged inside the shell, and is used for processing the electrical signal and extracting the earth boundary infrared radiation.

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

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

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

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

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

[0011] Shielding box for shielding electric signal;

[0012] Front end plate for amplifying front end electric signal;

[0013] Detector is infrared signal sensor for converting detected infrared signal of space into electric signal;

[0014] Detector pressing strip for fixing detector;

[0015] Detector mounting box for mounting and fixing detector;

[0016] Filter is germanium material for spectral filtering;

[0017] Filter pressing plate for fixing filter;

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

[0019] Preferably, shielding box is fastened and mounted at bottom of earth boundary infrared radiation detection unit through screw.

[0020] Preferably, front end plate and detector are fastened in detector mounting box through detector pressing strip and screw.

[0021] Preferably, filter is fixed in detector mounting box through filter pressing plate and screw.

[0022] Compared with prior art, the present application has the following advantages: through power supply unit of control unit, power supply unit is converted into required voltage; four earth boundary infrared radiation detection units receive infrared radiation from different parts of earth, through front end light signal conversion electric signal amplification unit and rear end electric signal information processing unit, different infrared radiation energy received by each detection unit is calculated to obtain space vehicle attitude, when all earth boundary infrared radiation detection units receive equal radiation energy through calculation, it indicates that attitude angle of spacecraft is zero, otherwise, it indicates that spacecraft has attitude deviation, four detection systems constitute two-dimensional axial deviation, the present application has strong orbit universality and wide detection range. BRIEF DESCRIPTION OF DRAWINGS

[0023] The accompanying drawings are included to provide a further understanding of the present application, and constitute a part of the specification, illustrate the present application and explain the principles of the present application, and do not constitute limitation of the present application.

[0024] In the drawings:

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

[0026] Figure 2 It is the main view of the present application.

[0027] Figure 3 It is the structure of the earth boundary infrared radiation detection unit in the present application.

[0028] Figure 4 It is the structure of the front optical signal conversion electric signal amplification unit in the present application.

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

[0030] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application; based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0031] Please refer to Figures 1-4 The linear array infrared earth sensor provided by the embodiments of the present application is an instrument for measuring earth infrared thermal radiation. The linear array infrared earth sensor comprises: an earth boundary infrared radiation detection unit 1, which is arranged on a shell 6 in four groups, and has a detection surface facing outward, and is used for receiving infrared radiation from different directions of space in the universe;

[0032] A front optical signal conversion electric signal amplification unit 2 is arranged in four groups inside the shell 6, and is used for converting optical signals detected by the earth boundary infrared radiation detection unit 1 into electric signals;

[0033] A rear end electric signal information processing unit 3 is arranged inside the shell 6, and is used for performing information processing on the electric signals and extracting earth boundary infrared radiation.

[0034] In the embodiment of the present application, four earth boundary infrared radiation detection units 1 respectively receive infrared radiation from different parts of the earth, and the different infrared radiation energy received by each earth boundary infrared radiation detection unit 1 is calculated through a front optical signal conversion and electrical signal amplification unit 2 and a rear electrical signal information processing unit 3, so as to obtain the space vehicle attitude. The four attitude angles of the earth infrared radiation are calculated, and the linear array infrared earth sensor obtains the corresponding attitude angle change through collection, processing and calculation to determine the attitude of the vehicle. The linear array infrared earth sensor is suitable for a vehicle orbit of 200-1000 km. The earth boundary infrared radiation detection unit 1 uses a wave band of 14-16.25 μm, can measure the space vehicle attitude range of ± 16°, and can measure the space vehicle attitude accuracy of 3σ: 0.05°.

[0035] The power supply unit 4 of the earth sensor is controlled by the control unit 5 to supply power, and the required voltage is converted through 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 energy received by each detection unit is calculated through a front optical signal conversion and electrical signal amplification unit 2 and a rear electrical signal information processing unit 3, so as to obtain the space vehicle attitude. When all the earth boundary infrared radiation detection units 1 receive equal radiation energy through calculation, it indicates that the space vehicle attitude angle is zero, otherwise it indicates that the space vehicle has attitude deviation. The four detection systems form a two-dimensional axial deviation. The sensor of the present application has strong orbit versatility and wide detection range.

[0036] In one embodiment of the present application, please refer to Figure 3 The earth boundary infrared radiation detection unit 1 includes a first lens 1-2, a spacer ring 1-3, a second lens 1-4, a first compression ring 1-5, a second compression ring 1-6, and a lens barrel 1-1 arranged on the shell 6. The first lens 1-2, the spacer ring 1-3, and the second lens 1-4 are tightly fixed in the lens barrel 1-1 by the first compression ring 1-5 and the second compression ring 1-6.

[0037] For example, the atmospheric radiation wave band of the earth is 14-16.25 μm, and the detection wave band of the earth boundary infrared radiation detection unit 1 is set to 14-16.25 μm. Thus, the position of the earth can be captured by detecting the infrared radiation of the earth atmosphere.

[0038] The measurable space vehicle attitude range of the earth boundary infrared radiation detection unit 1 is -16°-16°. The attitude angle refers to the pitch angle and roll angle of the spacecraft relative to the local vertical line of the earth during on-orbit operation.

[0039] The measurable space vehicle attitude accuracy of the earth boundary infrared radiation detection unit 1 is 3σ: 0.05°.

[0040] In the embodiment, the earth boundary infrared radiation enters into the infrared detector through the first lens 1-2 and the second lens 1-4 in the earth boundary infrared radiation detection unit 1, and the infrared radiation imaging is performed, and the four earth boundary infrared radiation detection units 1 jointly form the entire infrared earth boundary thermal radiation.

[0041] In an embodiment of the present application, referring to Figure 4 The front-end optical signal conversion electric signal amplification unit 2 comprises a shielding box 2-1, a front-end plate 2-2, a detector 2-4, a detector pressing strip 2-3, a detector mounting box 2-5, a filter 2-6, and a filter pressing plate 2-7.

[0042] The shielding box 2-1 is used for electric signal shielding; and the front-end plate 2-2 is used for front-end electric signal amplification.

[0043] The detector 2-4 is an infrared signal sensor, which is used for converting the detected infrared signal of the cosmic space into an electric signal; the detector pressing strip 2-3 is used for fixing the detector 2-4; the detector mounting box 2-5 is used for mounting and fixing the detector 2-4; the filter 2-6 is made of germanium and is used for spectral filtering; and the filter pressing plate 2-7 is used for fixing 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 arranged in the detector mounting box 2-5.

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

[0046] In the embodiment, the front-end optical signal conversion electric signal amplification unit 2 converts the optical signal detected by the earth boundary infrared radiation detection unit 1 into an electric signal, and the attitude and solution are performed through the rear-end electric signal information processing unit 3.

[0047] Working principle: through the control unit 5 to earth sensor power unit 4 power supply, through the power unit 4 into the required voltage conversion; four earth boundary infrared radiation detection unit 1 respectively from the earth different parts of the infrared radiation, through the front end of the optical signal conversion electric signal amplification unit 2 and the back end of the electric signal information processing unit 3, to each detection unit received different infrared radiation energy solution and obtained space vehicle attitude, when all earth boundary infrared radiation detection unit 1 through the solution received radiation energy is equal, indicates that the spacecraft attitude angle is zero, otherwise indicates that the spacecraft has attitude deviation, four detection system constitutes two-dimensional axial deviation.

[0048] It should be noted that in this document, the terms "first" and "second" and the like are used merely to distinguish one entity or action from another, without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises", "comprising", or any other variation thereof are used in this document to refer to a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can also include other elements not expressly listed or inherent to such process, method, article, or apparatus.

[0049] Although embodiments of the present application have been shown and described, it is to be understood that various modifications, substitutions, alternatives, and variations can be made in the embodiments without departing from the principles and spirit of the application, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A linear array infrared Earth sensor, characterized in that, include: Earth boundary infrared radiation detection unit (1), four sets are set on the shell (6), with the detection surface facing outward, to receive infrared radiation from different directions of space in the universe respectively; The front-end optical signal to electrical signal amplification unit (2) is set in four sets inside the housing (6) to convert the optical signal detected by the Earth boundary infrared radiation detection unit (1) into an electrical signal; The back-end electrical signal information processing unit (3) is located inside the housing (6) and is used to process the electrical signal and extract the infrared radiation of the Earth's boundary. The front-end optical signal to electrical signal amplification unit (2) includes: Shielding box (2-1), used for shielding electrical signals; Front-end board (2-2), used for front-end electrical signal amplification; The detectors (2-4) are infrared signal sensors used to convert the detected infrared signals from outer space into electrical signals; Detector retaining strip (2-3) is used to fix the detector (2-4); Detector mounting box (2-5) is used to mount and fix the detector (2-4); Filters (2-6) are made of germanium and are used for spectral filtering. Filter pressure plate (2-7) is used to fix the filter (2-6); The shielding box (2-1) is located at the bottom of the Earth boundary infrared radiation detection unit (1), the detector mounting box (2-5) is located inside the shielding box (2-1), and the filter (2-6), the front end plate (2-2), and the detector (2-4) are all located inside the detector mounting box (2-5). The Earth boundary infrared radiation detection unit (1) includes: 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 tube (1-1) disposed on the housing (6). 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); The measurable spacecraft attitude range of the Earth boundary infrared radiation detection unit (1) is -16° to 16°. It also includes a control unit (5) for supplying power to the power supply unit (4) of the linear infrared earth sensor via a cable, and converting the power supply unit (4) into the operating voltage required by the linear infrared earth sensor.

2. The linear array infrared Earth sensor according to claim 1, characterized in that, The shielding box (2-1) is fastened to the bottom of the Earth boundary infrared radiation detection unit (1) by screws.

3. A linear array infrared Earth sensor according to claim 1, characterized in that, The front-end board (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.

4. A linear array infrared Earth sensor according to claim 1, characterized in that, The filter (2-6) is fixed in the detector mounting box (2-5) by the filter pressure plate (2-7) and screws.

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