CN116674770A - Telescope thermal control method suitable for Lagrange point L2 aircraft - Google Patents
Telescope thermal control method suitable for Lagrange point L2 aircraft Download PDFInfo
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- CN116674770A CN116674770A CN202310599790.9A CN202310599790A CN116674770A CN 116674770 A CN116674770 A CN 116674770A CN 202310599790 A CN202310599790 A CN 202310599790A CN 116674770 A CN116674770 A CN 116674770A
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- 238000000034 method Methods 0.000 title claims abstract description 27
- 238000009413 insulation Methods 0.000 claims abstract description 19
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- 230000003287 optical effect Effects 0.000 claims description 16
- 238000009434 installation Methods 0.000 claims description 6
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- 229910000838 Al alloy Inorganic materials 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 239000006229 carbon black Substances 0.000 claims description 3
- 229910002804 graphite Inorganic materials 0.000 claims description 3
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- 239000012779 reinforcing material Substances 0.000 claims description 3
- 239000004642 Polyimide Substances 0.000 claims description 2
- 229920001721 polyimide Polymers 0.000 claims description 2
- 230000000191 radiation effect Effects 0.000 claims description 2
- 238000005070 sampling Methods 0.000 claims description 2
- 238000004088 simulation Methods 0.000 claims description 2
- 230000000149 penetrating effect Effects 0.000 claims 1
- 238000010586 diagram Methods 0.000 description 6
- 230000001629 suppression Effects 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 239000003973 paint Substances 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
- 238000003384 imaging method Methods 0.000 description 2
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- 230000009471 action Effects 0.000 description 1
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- 238000004891 communication Methods 0.000 description 1
- 238000011217 control strategy Methods 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
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- 238000011160 research Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B23/00—Telescopes, e.g. binoculars; Periscopes; Instruments for viewing the inside of hollow bodies; Viewfinders; Optical aiming or sighting devices
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation
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- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
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- General Health & Medical Sciences (AREA)
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- Biodiversity & Conservation Biology (AREA)
- Environmental & Geological Engineering (AREA)
- General Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
- Toxicology (AREA)
- Astronomy & Astrophysics (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Telescopes (AREA)
- Control Of Temperature (AREA)
Abstract
The invention provides a telescope thermal control method adapting to a Lagrange point L2 aircraft, which is characterized by comprising the following steps: s1, shielding direct irradiation of the sun in an L2 orbit by adopting a satellite sailboard, and coating a multi-layer heat insulation assembly on the outer surfaces of a space telescope shade and a main body; s2, designing a load temperature control cabin for the space telescope, wherein the telescope main body is arranged in the load temperature control cabin; s3, active temperature control is carried out on the bottom cabin plate of the telescope by adopting a PID high-precision temperature control algorithm based on pulse width modulation; s4, compensating radiation heat leakage of the primary mirror and the secondary mirror through the light inlet and the cold black background by roughly controlling and finely controlling the two types of heaters; s5, solving the problem of temperature uniformity by adopting a variable-heat-flow density heater for the telescope secondary mirror support truss.
Description
Technical Field
The invention relates to the technical field of thermal control of effective load of aircrafts, in particular to a high-stability thermal control method of an optical telescope of an L2 aircraft (called an L2 aircraft for short) adapting to a Lagrange point.
Background
At the Lagrangian point of the day, satellites can remain relatively stationary under the general attraction of the sun and the earth. Five points meeting the condition are arranged, the L1 point orbit is positioned between the sun and the earth, and the observation is deviated from the sun sky area and is easily shielded by the earth; the L3 point track is positioned on a solar earth connecting line, and is easily influenced by solar high-energy particles when communicating with the earth; the L4 and L5 point tracks are similar to the trailing track of the Japanese earth, are about 1.5 hundred million kilometers away from the earth, consume more fuel and have high communication cost. The L2 point orbit is positioned on an extension line of a day-to-ground connection line, has no influence of gravity gradient of the earth, can realize observation in the whole day, has a stable heat radiation environment, and is an ideal place for observing universe and astronomical research. A number of scientific satellites have been launched abroad that operate in the earth L2, such as the astronomical satellites "planck" and "hcher" launched by the european aerospace agency ESA, the american national aerospace agency NASA "james weber" space telescope.
For the celestial measurement technique of planetary detection, planetary measurement is realized by utilizing the relative position change between a target star and a reference star, and the measurement accuracy is generally required to reach the micro-angle second level. For telescope optical system technology, the stability of the optical system is of paramount importance. Due to the influences of factors such as telescope optics and structural material differences, temperature differences, external vibration and the like, the change of azimuth elements in the telescope is caused, and then the stability error of an optical system is caused. Therefore, a set of thermal control method which can adapt to the L2 track on the day and can realize the high-stability temperature control of the space optical telescope is designed according to the characteristics of the space environment of the L2 aircraft and in combination with the thermal control requirements of high precision and high stability.
Disclosure of Invention
Technical problem to be solved
Aiming at the celestial body measurement requirements of high-precision and high-stability thermal control of a space telescope, the invention provides a thermal control method of a space optical telescope of an L2 aircraft adapting to a solar-earth Lagrange point, and the method can realize accurate temperature control of each device of the space telescope of the L2 aircraft.
Technical proposal
In order to achieve the above purpose, the invention is realized by the following technical scheme:
the invention provides a thermal control method of a space telescope of an L2 aircraft adapting to a Lagrange point, which comprises the following steps:
s1, shielding direct irradiation of the sun in an L2 orbit by adopting a satellite sailboard, and coating a multi-layer heat insulation assembly on the outer surfaces of a space telescope shade and a main body;
s2, designing a load temperature control cabin for the space telescope, wherein the telescope main body is arranged in the load temperature control cabin;
s3, active temperature control is carried out on the bottom cabin plate of the telescope by adopting a PID high-precision temperature control algorithm based on pulse width modulation;
s4, compensating radiation heat leakage of the primary mirror and the secondary mirror through the light inlet and the cold black background by roughly controlling and finely controlling the two types of heaters;
s5, solving the problem of temperature uniformity by adopting a variable-heat-flow density heater for the telescope secondary mirror support truss;
further, the step S1 specifically includes: the space telescope light shield and the main body are both coated with 15 units of low-temperature multi-layer heat insulation components, and the outermost layer adopts a conductive polyimide silver-plated secondary surface mirror.
Further, step S2 specifically includes: the load temperature control cabin is an independent cabin body of the satellite platform, is made of aluminum alloy, is insulated from the satellite platform, and is stuck with an active heater for temperature control, and the temperature control target is 20 ℃. The outer surface of the temperature control cabin is coated with 15 units of multi-layer heat insulation components, and the inner surface is not specially treated.
Further, the thermal control method in step S3 adopts a special temperature controller to directly control according to the temperature data collected by the thermistor, the sampling period is 1S, the temperature control period is 5S, and the temperature is controlled to be 20.1 ℃.
Further, step S4 specifically includes disposing the coarse control and fine control heaters on the primary and secondary mirror support structures, and controlling the temperature of the lens by radiation action of the support structures. Considering that the primary mirror and the secondary mirror deviate from the target temperature in a single-phase way, the heaters are in a switch closed-loop mode, the index of the rough temperature control heater is 19-20 ℃, and the index of the fine temperature control heater is 20.1-20.12 ℃.
Further, step S5 specifically includes coating the multi-layer heat insulation component on the outer surface of the support truss between the primary mirror and the secondary mirror, where the outer surface of the multi-layer component adopts a carbon black permeable film in consideration of suppressing the influence of stray light. The active heater is stuck along the secondary mirror support truss to control the temperature, so that the heat flux density of the heater needs to be changed in order to prevent the temperature distribution with high two ends and low middle, the heat flux density distribution is set according to the simulation result, and the temperature uniformity problem of the support truss is solved. The temperature of the heater is controlled to be 20.1-20.12 ℃.
Further, the temperature control method for the telescope further comprises the following steps:
and pasting a graphite heat conduction strip reinforcing material heat conduction effect on a support rod frame of the telescope and coating a multi-layer heat insulation assembly, wherein the bottom of the support rod frame is an installation interface of the whole telescope load and the satellite platform.
Advantageous effects
The invention provides a thermal control method of an optical telescope of an L2 aircraft adapting to a solar-earth Lagrange point, which can realize accurate temperature control of each device of the telescope in the L2 aircraft according to satellite orbit characteristics and space detection requirements by adopting an active thermal control scheme, and can adapt to temperature control in various space flight states.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It is evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
FIG. 1 is a schematic diagram illustrating steps of a thermal control method for an optical telescope of an adaptive Lagrange point L2 aircraft according to an embodiment of the present invention;
FIG. 2 is a schematic diagram showing the installation position of a space telescope on a satellite according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of an overall thermal control scheme for a space telescope according to an embodiment of the present invention;
fig. 4 and 5 are schematic diagrams of a telescope primary and secondary mirror and truss structure thermal control design according to an embodiment of the present invention;
fig. 6 and fig. 7 are schematic diagrams of the position and thermal control design of the fold mirror 1 of the telescope according to an embodiment of the present invention;
FIG. 8 is a schematic diagram of the positions of the three mirrors, the folding mirror 2 and the folding mirror 3 of the telescope according to an embodiment of the present invention;
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It will be apparent that the described embodiments are some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Referring to fig. 1, an embodiment of the present invention provides a thermal control method for an aircraft adapted to a solar lagrangian point L2, comprising the steps of:
s1, shielding direct irradiation of the sun in an L2 orbit by adopting a satellite sailboard, and coating a multi-layer heat insulation assembly on the outer surfaces of a space telescope shade and a main body;
s2, designing a load temperature control cabin for the space telescope, wherein the telescope main body is arranged in the load temperature control cabin;
s3, active temperature control is carried out on the bottom cabin plate of the telescope by adopting a PID high-precision temperature control algorithm based on pulse width modulation;
s4, compensating radiation heat leakage of the primary mirror and the secondary mirror through the light inlet and the cold black background by roughly controlling and finely controlling the two types of heaters;
s5, solving the problem of temperature uniformity by adopting a variable-heat-flow density heater for the telescope secondary mirror support truss;
referring to fig. 2, a satellite sailboard is adopted to shield the direct irradiation of the sun in the L2 orbit, a space telescope light shield and the outer surface of a main body are coated with a plurality of layers of heat insulation components, and the telescope main body is arranged in a load temperature control cabin;
in this embodiment, the load temperature control cabin is made of aluminum alloy, a thin film heating plate is adhered to the surface of the load temperature control cabin, and the inner side and the outer side of the load temperature control cabin are both coated with the multilayer heat insulation components. The load temperature control cabin temperature control index is generally 20.1+/-0.5 ℃, is used for isolating the single-machine temperature interference of a platform and provides a stable thermal environment for effective load.
In this embodiment, the telescope is set in a reverse solar direction, and solar radiation heat flow is blocked by the sun shield and the satellite platform cabin. Among them, for a telescope, a long focal length, large caliber, high resolution space camera is generally required to reach or approach the diffraction limit, and the fine disturbance will have a significant effect on the imaging quality of the camera and is very sensitive to temperature change. In order to ensure imaging quality, the spatial telescope requires temperature control accuracy to be less than 45mK within 2 hours of each observation time.
In this embodiment, referring to fig. 3, the telescope is divided into two parts according to the external environment in which the telescope is located:
1) A radiant heat exchange zone: the part between the optical platform and the light inlet comprises a light shield, a primary mirror, a secondary mirror and a supporting structure thereof, which is called a radiation heat exchange area. Each component of the radiation heat exchange area has no heat consumption, and has radiation effect with the external cold and black background through the light inlet;
2) Interference suppression region: the remainder of the load, including the three mirrors, five mirrors and the support, is electronically referred to as the disturbance rejection zone. This is in close proximity to the enclosed space but is affected by satellite platform temperature fluctuations and telescope electronics. The radiation of the radiation heat exchange area to the space with deep cooling is compensated by a heater, and the temperature of the optical system component is controlled by adopting a switch-type heater control method in consideration of the stability of the external heat flow environment, wherein the temperature control range is 20.1-20.12 ℃. The temperature control of the interference suppression area generally adopts a two-stage temperature control method. The load temperature control cabin is designed on the satellite platform, active temperature control is carried out on each panel in the cabin, the load temperature control cabin is insulated with the satellite platform, the load temperature control cabin is used as a secondary temperature control object, the influence of the temperature of the platform is isolated, and the temperature control target is 20+/-0.5 ℃. The telescope interference suppression area is arranged in the load temperature control cabin, the bottom cabin plate of the telescope is used as a primary temperature control object, and the temperature is controlled by adopting a PID high-precision temperature control algorithm based on pulse width modulation. The focal plane detector is connected with the telescope main body in a heat-insulating way, the main body is coated with a multi-layer heat-insulating component, and heat is conducted to an external independent radiating surface through a loop heat pipe to be radiated independently. Based on the two-stage temperature control method, the radiating surface is used as a second-stage temperature control object, and the detector case is used as a first-stage temperature control object, so that high-stability temperature control is realized.
In this embodiment, referring to fig. 4 and 5, a temperature control method for a radiation heat exchange area includes:
1) And a coarse temperature control heater and a fine temperature control heater are respectively arranged on a main mirror supporting structure and a secondary mirror supporting structure of the telescope, the coarse temperature control heater is normally open, and the fine temperature control heater adopts a switch temperature control strategy. The main mirror and the secondary mirror of the telescope perform radiation temperature control through the back support structure to compensate radiation heat leakage to the space. The front of the primary and secondary environments is extremely low emissivity of 0.05, and the back is high emissivity of 0.9. The primary and secondary supporting structures are sprayed with black paint, and are high-emissivity surfaces, and a multi-layer heat insulation assembly is coated between the supporting structure and the side surface of the secondary supporting structure to form a closed cavity.
2) And designing a variable heat flux thin film heater, adhering along a secondary mirror support truss of the telescope, and actively controlling the temperature of the support truss between the primary mirror and the secondary mirror of the telescope. Wherein, the support truss cladding multilayer heat insulation component between the major and minor mirror, the influence of taking into account suppressing stray light, multilayer subassembly surface adopts oozing carbon black membrane.
3) The outer side of the bracket of the folding mirror 1 is coated with a plurality of layers of heat insulation components except the light inlet, and the inner side is sprayed with black paint. The folding mirror 1 is located inside the main mirror hole and is fixed by a bracket installed on the optical platform, as shown in fig. 6 and 7 below.
In this embodiment, the temperature control method for the interference suppression area includes:
1) And spraying high-emissivity black paint on the inner part of the bottom cabin of the telescope, arranging an active heater on the outer part of the cabin, and coating a multi-layer heat insulation assembly. As shown in FIG. 8, the three mirrors, the folding mirror 2 and the folding mirror 3 are positioned in the bottom cabin of the telescope, are relatively closed, and have relatively stable thermal environment.
2) And pasting a graphite heat conduction strip reinforcing material heat conduction effect on a support rod frame of the telescope and coating a multi-layer heat insulation assembly, wherein the bottom of the support rod frame is an installation interface of the whole telescope load and the satellite platform. The bottom of the support rod frame of the telescope is an installation interface of the whole telescope load and the satellite platform, the installation interface is positioned in the load temperature control cabin, and the interface temperature is 20+/-0.5 ℃.
The above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; these modifications or substitutions do not depart from the essence of the corresponding technical solutions from the protection scope of the technical solutions of the embodiments of the present invention.
Claims (7)
1. A telescope thermal control method suitable for a Lagrange point L2 aircraft is characterized by comprising the following steps:
s1, shielding direct irradiation of the sun in an L2 orbit by adopting a satellite sailboard, and coating a multi-layer heat insulation assembly on the outer surfaces of a space telescope shade and a main body;
s2, designing a load temperature control cabin for the space telescope, wherein the telescope main body is arranged in the load temperature control cabin;
s3, active temperature control is carried out on the bottom cabin plate of the telescope by adopting a PID high-precision temperature control algorithm based on pulse width modulation;
s4, compensating radiation heat leakage of the primary mirror and the secondary mirror through the light inlet and the cold black background by roughly controlling and finely controlling the two types of heaters;
s5, adopting a variable-heat-flow density heater for the telescope secondary mirror support truss.
2. The method for thermally controlling the high stability of an optical telescope of an adaptive solar lagrangian point L2 aircraft according to claim 1, wherein step S1 comprises: the space telescope light shield and the main body are both coated with 15 units of low-temperature multi-layer heat insulation components, and the outermost layer adopts a conductive polyimide silver-plated secondary surface mirror.
3. The method for thermally controlling the high stability of an optical telescope of an adaptive solar lagrangian point L2 aircraft according to claim 1, wherein step S2 comprises: the load temperature control cabin is an independent cabin body of the satellite platform, is made of aluminum alloy, is insulated from the satellite platform, and is stuck with an active heater for temperature control on a temperature control cabin plate, and the temperature control target is 20 ℃; the outer surface of the temperature control cabin is coated with 15 units of multi-layer heat insulation components.
4. The method for thermally controlling the high stability of the optical telescope of the L2 aircraft adapted to the solar lagrangian point according to claim 1, wherein the thermal control method in step S3 uses a dedicated temperature controller to directly control the optical telescope according to the temperature data collected by the thermistor, the sampling period is 1S, the temperature control period is 5S, and the temperature control target is 20.1 ℃.
5. The method of claim 1, wherein step S4 comprises: the rough control and fine control heaters are arranged on the main mirror supporting structure and the secondary mirror supporting structure, and the temperature of the lenses is controlled through the radiation effect of the supporting structures; the heaters are all in a switch closed loop mode, the index of the coarse temperature control heater is 19-20 ℃, and the index of the fine temperature control heater is 20.1-20.12 ℃.
6. The method for thermally controlling the high stability of an optical telescope of an adaptive solar lagrangian point L2 aircraft according to claim 1, wherein step S5 comprises: the multi-layer heat insulation component is wrapped outside the support truss between the primary mirror and the secondary mirror, and the influence of stray light is restrained, wherein a carbon black penetrating film is adopted on the outer surface of the multi-layer component. The active heater is stuck along the secondary mirror support truss to control the temperature, so that the heat flux density of the heater needs to be changed in order to prevent the temperature distribution with high two ends and low middle, the heat flux density distribution is set according to the simulation result, and the temperature uniformity problem of the support truss is solved. The temperature of the heater is controlled to be 20.1-20.12 ℃.
7. The thermal control method of an adaptive earth lagrangian point L2 aircraft of claim 1, wherein the method of controlling the temperature of the telescope further comprises:
and pasting a graphite heat conduction strip reinforcing material heat conduction effect on a support rod frame of the telescope and coating a multi-layer heat insulation assembly, wherein the bottom of the support rod frame is an installation interface of the whole telescope load and the satellite platform.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310599790.9A CN116674770A (en) | 2023-05-25 | 2023-05-25 | Telescope thermal control method suitable for Lagrange point L2 aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202310599790.9A CN116674770A (en) | 2023-05-25 | 2023-05-25 | Telescope thermal control method suitable for Lagrange point L2 aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116986020A (en) * | 2023-09-26 | 2023-11-03 | 长光卫星技术股份有限公司 | Small satellite active thermal control method based on thermal characteristics of controlled object |
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2023
- 2023-05-25 CN CN202310599790.9A patent/CN116674770A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116986020A (en) * | 2023-09-26 | 2023-11-03 | 长光卫星技术股份有限公司 | Small satellite active thermal control method based on thermal characteristics of controlled object |
| CN116986020B (en) * | 2023-09-26 | 2023-12-01 | 长光卫星技术股份有限公司 | Small satellite active thermal control method based on thermal characteristics of controlled object |
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