CN112666670B - Active thermal control device and method of space optical remote sensor - Google Patents
Active thermal control device and method of space optical remote sensor Download PDFInfo
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- CN112666670B CN112666670B CN201910943011.6A CN201910943011A CN112666670B CN 112666670 B CN112666670 B CN 112666670B CN 201910943011 A CN201910943011 A CN 201910943011A CN 112666670 B CN112666670 B CN 112666670B
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Abstract
The invention provides an active thermal control device of a space optical remote sensor, which comprises a primary mirror assembly, a secondary mirror assembly, a three-mirror assembly and a primary mirror thermal control assembly, wherein the primary mirror thermal control assembly comprises an inner ring control assembly and an outer ring control assembly; the outer ring control assembly comprises a first controller, a second controller, a heating plate, a main mirror supporting structure, a main mirror and a first temperature detector which are sequentially connected in a ring shape; the inner ring control assembly comprises a second controller, the heating plate, the main mirror support and a second temperature detector, one end of the second temperature detector is arranged between the first controller and the second controller, and the other end of the second temperature detector is arranged between the main mirror and the main mirror support. The invention adopts the double closed loops to control the temperature of the optical remote sensor, so that the controller can more accurately control the temperature of the optical remote sensor. And then can guarantee that the change of the image focal plane position of the optical remote sensor is smaller, make its image quality better.
Description
Technical Field
The invention relates to the field of space remote sensors, in particular to an active thermal control device and method of a space optical remote sensor.
Background
The space optical remote sensor is used as an effective load of a remote sensing satellite, and can generate large temperature difference due to the fact that the space optical remote sensor is easily affected by thermal factors such as space heat sink, solar radiation and earth infrared radiation after the space optical remote sensor enters an orbit to work. The large temperature difference influences the normal work of the electronic part of the remote sensor, and also generates thermal disturbance to influence the imaging quality of an optical system. Therefore, there is a need for an optimized design for remote sensors that implement thermal control. The current thermal control strategy mainly comprises two modes of active thermal control and passive thermal control, and the difference is that the passive thermal control has no feedback effect on a temperature control system by a controlled object in the control process, and the active thermal control can implement a temperature control and temperature measurement component on a structural part of a remote sensor and adjust the temperature according to the change of internal and external heat flows to form closed-loop control.
In the current thermal control method, passive thermal control belongs to open-loop control, and the optical remote sensor is in a required temperature range by setting target temperature of the optical remote sensor and reasonably thermally controlling the structure. The temperature monitoring device has the defects that the controller cannot realize real-time monitoring of the temperature of the key part of the remote sensor, the temperature can only be controlled within a certain range, and high-precision temperature control cannot be realized. The active thermal control is characterized in that the temperature sensor is used for collecting the temperature of the key part of the remote sensor and feeding the temperature back to the controller, the controller is used for resolving the fed-back temperature, and a control signal is sent to the heating sheet to control the temperature of the optical remote sensor to reach a stable state, so that closed-loop control is formed. Thereby enabling the device to function properly. Although such closed loop control can monitor the temperature of critical parts of the remote sensor in real time, the control accuracy of a single closed loop is not ideal.
Disclosure of Invention
The invention aims to provide an active thermal control device of a space optical remote sensor, which aims to solve the technical problem that the closed-loop control precision is not ideal in the prior art.
The second purpose of the invention is to provide an active thermal control method of a space optical remote sensor, which has more accurate temperature control, small change of the position of an imaging focal plane of the optical remote sensor and good imaging quality.
In order to solve the technical problem, on one hand, the invention provides an active thermal control device of a space optical remote sensor, which comprises a primary mirror assembly, a secondary mirror assembly, a three-mirror assembly and a primary mirror thermal control assembly, wherein the primary mirror thermal control assembly comprises an inner ring control assembly and an outer ring control assembly; the outer ring control assembly comprises a first controller, a second controller, a heating plate, a main mirror supporting structure, a main mirror and a first temperature detector which are sequentially connected in a ring shape; the inner ring control assembly comprises a second controller, the heating plate, the main mirror support and a second temperature detector, one end of the second temperature detector is arranged between the first controller and the second controller, and the other end of the second temperature detector is arranged between the main mirror and the main mirror support.
In another aspect, the present invention provides an active thermal control method for a space optical remote sensor, where the active thermal control method for a space optical remote sensor includes:
s1, inputting a target temperature to a first controller, and judging whether to control the temperature of a primary mirror supporting assembly or not by a second controller through receiving data fed back by a second temperature detector when first thermal disturbance exists between a heating sheet and a primary mirror supporting mechanism so as to realize inner loop control;
and S2, when second thermal disturbance exists between the main mirror supporting mechanism and the main mirror, the temperature of the main mirror is fed back to the first controller through the first temperature detector and is transmitted to the heating plate through the second controller, and therefore outer ring control is achieved.
Further, the second controller in step S1 judges whether to perform temperature control on the primary mirror support assembly by receiving data fed back by the second temperature detector, so that the specific steps of implementing inner loop control are as follows:
s11, when the feedback temperature of the second temperature detector is higher than the target temperature, the second controller controls the heating sheet not to heat;
and S12, when the feedback temperature of the second temperature detector is lower than the target temperature, the second controller heats the main mirror supporting structure through the heating sheet.
Further, in the step S2, the feedback is sent to the first controller through the first temperature detector, and the feedback is sent to the heating plate through the second controller, so that the specific steps of realizing the outer loop control are as follows:
s21, when the temperature of the first temperature detector is lower than the target temperature, the second controller heats the main mirror supporting mechanism through the heating sheet;
and S22, when the temperature of the first temperature detector is higher than the target temperature, the second controller controls the heating sheet not to heat.
The invention has the beneficial effects that: the invention adopts double closed-loop control, and through the control strategy, the first thermal disturbance is inhibited twice, and the second thermal disturbance is inhibited once; the width of the inner ring is large, and the response is fast; the outer loop response is slow; through separately controlling first controller and second controller, control the inner ring earlier to the inner ring is adjusted, has controlled the outer ring again, and control parameter easily adjusts, and is more accurate to control accuracy, guarantees that remote sensor imaging quality is better.
Drawings
Fig. 1 is a schematic diagram of an active thermal control scheme according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
In order to make the description of the present disclosure more complete and complete, the following description is given for illustrative purposes with respect to the embodiments and examples of the present invention; it is not intended to be the only form in which the embodiments of the invention may be practiced or utilized. The embodiments are intended to cover the features of the various embodiments as well as the method steps and sequences for constructing and operating the embodiments. However, other embodiments may be utilized to achieve the same or equivalent functions and step sequences.
Example 1:
the optical imaging system of the space optical remote sensor is analyzed, and found that the optical components influencing the focal plane position of the optical imaging system comprise a primary mirror component, a secondary mirror component and a three-mirror component, the primary mirror component has the largest influence on the focal plane position, and the three-mirror component has the smallest influence on the focal plane position. Since the primary mirror is a key component in the optical imaging system of the remote sensor, dual closed loop control should be implemented on the primary mirror assembly. Meanwhile, in order to avoid the temperature overshoot of the secondary mirror and the tertiary mirror assembly and ensure the imaging quality of the remote sensor, the temperatures of the secondary mirror and the tertiary mirror assembly are adjusted along with the temperature of the primary mirror assembly, so that the whole optical assembly reaches temperature balance.
The active thermal control device of the space optical remote sensor in the embodiment comprises a primary mirror assembly, a secondary mirror assembly and a three-mirror assembly, wherein the primary mirror thermal control assembly comprises an inner ring control assembly and an outer ring control assembly; the outer ring control assembly comprises a first controller, a second controller, a heating plate, a main mirror supporting structure, a main mirror and a first temperature detector which are sequentially connected in a ring shape; the inner ring control assembly comprises a second controller, a heating plate, a main mirror support and a second temperature detector, wherein one end of the second temperature detector is arranged between the first controller and the second controller, and the other end of the second temperature detector is arranged between the main mirror and the main mirror support.
Example 2:
an active thermal control method of a space optical remote sensor, which uses an active thermal control device of the space optical remote sensor, and the method comprises the following steps:
s1, inputting a target temperature to a first controller, and judging whether to control the temperature of a main mirror supporting assembly or not by a second controller through receiving data fed back by a second temperature detector when first thermal disturbance exists between a heating plate and a main mirror supporting mechanism so as to realize inner loop control;
and S2, when second thermal disturbance exists between the main mirror supporting mechanism and the main mirror, the temperature of the main mirror is fed back to the first controller through the first temperature detector and is transmitted to the heating plate through the second controller, and therefore outer ring control is achieved.
The second controller in step S1 judges whether to perform temperature control on the primary mirror support assembly by receiving data fed back by the second temperature detector, so that the specific steps of implementing inner loop control are as follows:
s11, when the feedback temperature of the second temperature detector is higher than the target temperature, the second controller controls the heating sheet not to heat;
and S12, when the feedback temperature of the second temperature detector is lower than the target temperature, the second controller heats the main mirror supporting structure through the heating sheet.
In the step S2, the feedback is sent to the first controller through the first temperature detector, and the feedback is sent to the heating plate through the second controller, so that the specific steps of realizing the outer loop control are as follows:
s21, when the temperature of the first temperature detector is lower than the target temperature, the second controller heats the main mirror supporting mechanism through the heating sheet;
and S22, when the temperature of the first temperature detector is higher than the target temperature, the second controller controls the heating sheet not to heat.
The control priority of the inner ring and the outer ring is to perform inner ring control first and then perform outer ring control, so that the control parameters are easy to adjust, and the control precision is more accurate.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention, and that variations, modifications, substitutions and alterations can be made to the above embodiments by those of ordinary skill in the art within the scope of the present invention.
The above embodiments of the present invention should not be construed as limiting the scope of the present invention. Any other corresponding changes and modifications made according to the technical idea of the present invention should be included in the protection scope of the claims of the present invention.
Claims (2)
1. An active thermal control method of a space optical remote sensor is characterized by comprising the following steps:
s1, inputting a target temperature to a first controller, and judging whether to control the temperature of a main mirror supporting assembly or not by a second controller through receiving data fed back by a second temperature detector when first thermal disturbance exists between a heating plate and a main mirror supporting mechanism so as to realize inner loop control;
s2, when second thermal disturbance exists between the main mirror supporting mechanism and the main mirror, the temperature of the main mirror is fed back to the first controller through the first temperature detector and is transmitted to the heating plate through the second controller, and therefore outer ring control is achieved;
the second controller in step S1 judges whether to perform temperature control on the primary mirror support assembly by receiving data fed back by the second temperature detector, so that the specific steps of implementing inner loop control are as follows:
s11, when the feedback temperature of the second temperature detector is higher than the target temperature, the second controller controls the heating sheet not to heat;
s12, when the feedback temperature of the second temperature detector is lower than the target temperature, the second controller heats the main mirror supporting structure through the heating sheet;
in the step S2, the feedback to the first controller is provided through the first temperature detector, and the feedback is provided to the heating sheet through the second controller, so that the specific steps of realizing the outer loop control are as follows:
s21, when the temperature of the first temperature detector is lower than the target temperature, the second controller heats the main mirror supporting mechanism through the heating sheet;
and S22, when the temperature of the first temperature detector is higher than the target temperature, the second controller controls the heating sheet not to heat.
2. The device for realizing the active thermal control method of the space optical remote sensor is characterized by comprising a primary mirror assembly, a secondary mirror assembly and a three-mirror assembly, wherein the primary mirror thermal control assembly comprises an inner ring control assembly and an outer ring control assembly; the outer ring control assembly comprises a first controller, a second controller, a heating plate, a main mirror supporting structure, a main mirror and a first temperature detector which are sequentially connected in a ring shape; the inner ring control assembly comprises a second controller, the heating plate, the main mirror support and a second temperature detector, one end of the second temperature detector is arranged between the first controller and the second controller, and the other end of the second temperature detector is arranged between the main mirror and the main mirror support.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5627927A (en) * | 1992-10-20 | 1997-05-06 | Mcdonnell Douglas Aerospace West | Fiber with multiple overlapping gratings |
| CN103335651A (en) * | 2013-06-19 | 2013-10-02 | 北京航空航天大学 | Double-speed-ring control method of aerial remote sensing inertial-stabilized platform |
| CN103616790A (en) * | 2013-11-25 | 2014-03-05 | 中国科学院长春光学精密机械与物理研究所 | Space camera initiative thermal control method based on temperature levels |
| CN106643194A (en) * | 2016-12-30 | 2017-05-10 | 四川航天拓鑫玄武岩实业有限公司 | Temperature control system and method for basalt electric boosting melting kiln |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104029129A (en) * | 2014-06-06 | 2014-09-10 | 中国科学院长春光学精密机械与物理研究所 | Polishing solution constant-temperature feeding device for optical machining and temperature control method |
| CN104516087B (en) * | 2014-12-17 | 2017-06-09 | 中国科学院长春光学精密机械与物理研究所 | A kind of sandwich-type precision thermal controls apparatus for space optical remote sensor speculum |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5627927A (en) * | 1992-10-20 | 1997-05-06 | Mcdonnell Douglas Aerospace West | Fiber with multiple overlapping gratings |
| CN103335651A (en) * | 2013-06-19 | 2013-10-02 | 北京航空航天大学 | Double-speed-ring control method of aerial remote sensing inertial-stabilized platform |
| CN103616790A (en) * | 2013-11-25 | 2014-03-05 | 中国科学院长春光学精密机械与物理研究所 | Space camera initiative thermal control method based on temperature levels |
| CN106643194A (en) * | 2016-12-30 | 2017-05-10 | 四川航天拓鑫玄武岩实业有限公司 | Temperature control system and method for basalt electric boosting melting kiln |
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