阅读说明：本技术 一种切入式星载大视场红外相机定标机构 (Cut-in type satellite-borne large-visual-field infrared camera calibration mechanism ) 是由 陈凡胜 孙小进 赵学琴 郝俊川 于 2019-11-11 设计创作，主要内容包括：本发明公开了一种切入式星载大视场红外相机定标机构。该定标机构包括：锁定机构、手动锁定杆、拔销器、黑体碳纤维罩、黑体、轴承、圆柱压缩弹簧、步进电机和谐波减速器、锁定轴、连接块。发射时选用锁定机构对定标机构锁住,卫星进入轨道后再解锁。黑体在黑体碳纤维罩内升温至设定的定标温度后,由步进电机驱动黑体切入光路进行定标；考虑到装置的可靠性,在定标机构中加入了圆柱压缩弹簧,圆柱压缩弹簧的扭矩大于电机断电时的自定位力矩且小于电机正常工作的输出力矩,由此在断电时,圆柱压缩弹簧可将黑体从光路中拉出。该发明解决了黑体时转动引起损坏、加热过程中系统不能进行探测以及断电时定标黑体切出光路的可靠性问题。(The invention discloses a cut-in type satellite-borne large-view-field infrared camera calibration mechanism. The calibration mechanism comprises: the device comprises a locking mechanism, a manual locking rod, a pin puller, a black body carbon fiber cover, a black body, a bearing, a cylindrical compression spring, a stepping motor, a harmonic reducer, a locking shaft and a connecting block. And during launching, the calibration mechanism is locked by a locking mechanism, and the satellite enters the orbit and then is unlocked. After the blackbody is heated to a set calibration temperature in the blackbody carbon fiber cover, the step motor drives the blackbody to cut into the light path for calibration; in consideration of the reliability of the device, a cylindrical compression spring is added in the calibration mechanism, the torque of the cylindrical compression spring is larger than the self-positioning torque when the motor is powered off and smaller than the output torque of the normal work of the motor, and therefore the black body can be pulled out of a light path by the cylindrical compression spring when the motor is powered off. The invention solves the problems of damage caused by rotation of the black body, incapability of detecting a system in a heating process and reliability of a calibration black body cut-out light path in power failure.)

1. A cut-in satellite-borne large-field-of-view infrared camera calibration mechanism comprises: the device comprises a locking mechanism (1), a manual locking rod (2), a pin puller (3), a black body carbon fiber cover (4), a black body (5), a bearing (6), a cylindrical compression spring (7), a stepping motor, a harmonic reducer (8), a locking shaft (9) and a connecting block (10); it is characterized in that the preparation method is characterized in that,

the black body (5) is positioned at the long end of the swing arm of the calibration mechanism, the black body (5) and the swing arm are insulated through a polyimide heat insulation pad, and the other end of the swing arm of the calibration mechanism is connected with a driving mechanism of the calibration mechanism;

locking mechanical system (1) is installed in black body carbon fiber cover (4) outside, and locking mechanical system (1) includes: the locking device comprises a locking shaft (9), a cylindrical compression spring (7), a connecting block (10) and a pin puller (3);

the locking shaft (9) is positioned in a cylindrical shell of the locking mechanism, penetrates through a cylindrical compression spring (7), moves downwards under the action of manual operation, and compresses the spring (7), a groove is designed in the locking shaft (9), when the groove reaches the position of the pin puller (3), a pin of the pin puller (3) pops up to clamp the locking shaft (9), at the moment, the lower end of the locking shaft penetrates through a locking hole of a swinging arm of the black body (5) to lock the black body onto the black body carbon fiber cover (4), and the pin puller (3) is not electrified in a locking state; the pin puller (3) is installed on the connecting block (10), and the connecting block (10) is fixedly connected with the black body carbon fiber cover (4). When the black body (5) needs to be unlocked, the pin extractor (3) is electrified, the pin of the pin extractor (3) retracts, the locking shaft (9) is not restrained under the action of the cylindrical compression spring (7) and is restored to the position before unlocking, and the unlocking action of the black body (5) is realized; the locking mechanism (1) is used only for the satellite launch process. Ground transition transportation and test process adopt manual locking lever (2) to lock, and manual locking lever (2) lower extreme is helicitic texture, through revolving wrong manual locking lever (2), carries out threaded connection with another screw thread locking hole of black body (5) swing arm, realizes the manual locking of black body (5). The reverse-screwing manual locking rod (2) is unlocked from the threaded connection with the swing arm threaded locking hole, so that manual unlocking is realized;

the black body carbon fiber cover (4) is of a cavity structure and is arranged on a fixed support of the calibration device, one side of the black body carbon fiber cover (4) is closed, and a cut-in notch is reserved on the other side of the black body carbon fiber cover; in the non-calibration mode, the black body (5) is positioned in the cavity of the black body carbon fiber cover (4), the black body (5) completes the heating and cooling processes of the black body in the black body carbon fiber cover (4), and the black body carbon fiber cover (4) enables the black body (5) to be thermally isolated from the optical system, so that the influence of the temperature change of the black body (5) on the temperature control of the optical system is prevented, and the heating or cooling efficiency of the black body (5) is improved;

the stepping motor, the harmonic reducer (8), the bearing (6) and the swing arm of the black body (5) form a driving mechanism of the calibration device; when the optical system needs to perform infrared radiation calibration, the stepping motor (8) drives the swing arm to rotate and cut into the light path, and when the radiation calibration is finished, the stepping motor (8) drives the swing arm to rotate and cut out from the light path and return to the cavity of the black body carbon fiber cover (4), so that the radiation calibration process is completed; the calibration mechanism adopts open loop control, the stepping motor (8) drives the black body (5) to cut in and out a light path, and the position of the black body (5) is fed back through the Hall sensor to realize a calibration mode and a non-calibration mode.

2. The cut-in satellite-borne large-field-of-view infrared camera calibration mechanism according to claim 1, characterized in that: the torque of the cylindrical compression spring (7) is larger than the lower self-positioning torque when the motor is powered off and smaller than the output torque of the motor in normal operation.

Technical Field

The invention relates to the technical field of infrared radiation calibration, in particular to a cut-in type satellite-borne large-view-field infrared camera calibration mechanism.

Background

Radiometric calibration is the main means for monitoring instrument performance and is also the important basis for remote sensing data quantification application. The response of the infrared detector is greatly influenced by the environment, and a calibration coefficient of a laboratory is used, so that a large error can be introduced, and calibration parameters need to be updated continuously. On-satellite blackbody calibration is a common means for on-orbit calibration, and satellites such as Landsat 7 and 8 and Modis all adopt on-satellite blackbody calibration devices.

During satellite launching and orbit transfer, random force causes unbalanced moment, further causes rotation of the calibration body, and may cause damage to the black body, so that specific locking or protection measures are used to protect the black body. When the starry black body is used for calibrating a system with a large view field, the direction of the scanning mirror is usually changed, and the switching between the calibration mode and the observation mode of the detection system is realized. But the detector can not normally detect in the blackbody heating process, so that the effective detection time of the detector on the track is shortened. In addition, if a fault such as power failure occurs in the scanning mirror, the direction of the scanning mirror cannot be changed, the observation mode cannot be changed, and the problem of reliability exists.

Disclosure of Invention

In order to overcome the defects of the prior art, the invention provides a cut-in type satellite-borne large-view-field infrared camera calibration mechanism, which solves the problems that the rotation is damaged when a black body is emitted, a heating process system cannot carry out normal detection and the reliability of a calibration black body cut-in and cut-out light path is high. The calibration mechanism comprises: the device comprises a locking mechanism 1, a manual locking rod 2, a pin puller 3, a black body carbon fiber cover 4, a black body 5, a bearing 6, a cylindrical compression spring 7, a stepping motor and harmonic reducer 8, a locking shaft 9 and a connecting block 10;

black body 5 is located the long end of calibration mechanism swing arm, and black body 5 insulates against heat through the polyimide heat insulating mattress with the swing arm. The other end of the swing arm of the calibration mechanism is connected with a driving mechanism of the calibration mechanism;

locking mechanical system 1 installs in the 4 outsides of black body carbon fiber cover, and locking mechanical system 1 includes: a locking shaft (9), a cylindrical compression spring 7, a connecting block 10 and a pin puller 3;

locking shaft 9 is located inside the cylindrical casing of locking mechanical system, and the locking shaft passes cylindrical compression spring 7, and locking shaft moves down under manual action, compresses spring 7 simultaneously, and the design has a recess on the locking shaft 9, and when the recess reachd the position of pin puller 3, the pin of pin puller 3 pops out and blocks locking shaft 9, and the lower extreme of locking shaft passes the locking hole of 5 swing arms of black body this moment, locks the black body on black body carbon fiber cover 4, and this locking state pin puller 3 does not switch on. Pin remover 3 installs on connecting block 10, and connecting block 10 and black body carbon fiber cover 4 fixed connection. When the black body 5 needs to be unlocked, the pin puller 3 is electrified, the pin of the pin puller 3 retracts, the locking shaft 9 is not restrained under the action of the cylindrical compression spring 7 and returns to the position before unlocking, and the unlocking action of the black body 5 is realized; the locking mechanism 1 is used only for the satellite launch process. Ground transition transportation and test process adopt manual locking lever 2 to lock, and 2 lower extremes of manual locking lever are helicitic texture, through twisting manual locking lever 2 soon, carry out threaded connection with another screw thread locking hole of black body 5 swing arm, realize the manual locking of black body 5. The reverse-screwing manual locking rod 2 is unlocked from the threaded connection with the swing arm threaded locking hole, so that manual unlocking is realized;

black body carbon fiber cover 4 is the cavity structures, installs on calibration device's fixed bearing, and black body carbon fiber cover 4 one side is sealed, and the breach that cuts into the cutting is left to the opposite side. In the non-calibration mode, the black body 5 is positioned in the cavity of the black body carbon fiber cover 4, the black body 5 completes the heating and cooling processes of the black body in the black body carbon fiber cover 4, and the black body carbon fiber cover 4 enables the black body 5 to be thermally isolated from the optical system, so that the influence of the temperature change of the black body 5 on the temperature control of the optical system is prevented, and the heating or cooling efficiency of the black body 5 is improved;

compared with the prior art, the invention has the beneficial effects that:

1. the heating of black body 5 adopts thermal-insulated design in black body carbon fiber cover 4, and the heating process of black body 5 does not influence and surveys, has effectively prolonged the detector and has surveyed the time on the orbit.

2. The cylindrical compression spring 7 is added in the calibration mechanism, when the power is off, the black body 5 can be pulled out from the light path by the cylindrical compression spring 7, the calibration mode is switched out, and the reliability is high.

3. When the satellite launches and shifts the orbit, choose for use locking mechanical system 1 to pin the calibration mechanism, avoided the unbalanced moment that random force arouses, and then arouse the rotation of calibration body, cause the damage of black body 5.

Drawings

Fig. 1 is a schematic diagram of a scaling structure in a non-scaling mode.

Fig. 2 is a diagram illustrating a scaling structure of a scaling mode.

Fig. 3 is a schematic view of the pin puller.

Detailed Description

The invention is further described below with reference to the accompanying drawings.

A cut-in type satellite-borne large-visual-field infrared camera calibration mechanism comprises a locking mechanism 1, a manual locking rod 2, a pin puller 3, a black body carbon fiber cover 4, a black body 5, a bearing 6, a cylindrical compression spring 7, a stepping motor, a harmonic reducer 8, a locking shaft 9 and a connecting block 10. When the satellite launches and transfers the orbit, the unbalanced moment caused by random force is considered, and then the rotation of the calibration body is caused, so that the black body 5 is damaged. The locking mode is two, including that the black body 5 is in the black body carbon fiber cover 4 when the track is launched and transferred, the pin puller 2 is locked, and the black body is unlocked after the track is entered; and manual locking and unlocking are carried out in the ground installation and adjustment and transportation process. The calibration mechanism adopts open-loop control, the stepping motor can drive the black body 5 to cut in and out a light path, and the position of the black body 5 is fed back through the Hall sensor, so that a calibration mode and a non-calibration mode are realized. The heating of black body adopts thermal-insulated design in black body carbon fiber cover 4, and the heating process of black body 5 does not influence and surveys. In the non-calibration mode, the black body 5 is in the black body carbon fiber cover 4; in the calibration mode, the black body is in the optical path.

The calibration mechanism adopts open-loop control, the stepping motor can drive the black body to rotate around the motor shaft to move back and forth +/-75 degrees, a light path is cut in and out, and the position of the black body is fed back through the Hall sensor, so that a calibration mode and a non-calibration mode are realized. In the non-calibration mode, the black body 5 is in the black body carbon fiber cover 4; in the calibration mode, the black body 5 is in the optical path. Before calibration is carried out, the temperature of the on-satellite black body 5 in the black body carbon fiber cover 4 is raised to 100 ℃ through the on-satellite temperature control circuit, at the moment, the stepping motor drives the black body 5 to cut into a light path, and the position of the black body is fed back through the Hall sensor, so that an on-satellite calibration mode is realized. The position relation of each part of the calibration mechanism in the calibration mode is shown in figure 1, and after calibration is completed, the stepping motor drives the black body 5 to cut out a light path and enter the black body carbon fiber cover 4. The positional relationship of the parts of the scaling mechanism in the non-scaling mode is shown in fig. 2.

In consideration of the reliability of the device, the cylindrical compression spring 6 is added on the calibration mechanism, the torque of the cylindrical compression spring 6 is larger than the lower self-positioning torque when the motor is powered off and smaller than the output torque of the normal work of the motor, and the black body 5 can cut out a calibration light path in a mode that the cylindrical compression spring 6 is pulled out when the power is off.