CN111959830B - Thermal control system and method for satellite high-precision optical load mounting platform - Google Patents
Thermal control system and method for satellite high-precision optical load mounting platform Download PDFInfo
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- CN111959830B CN111959830B CN202010857201.9A CN202010857201A CN111959830B CN 111959830 B CN111959830 B CN 111959830B CN 202010857201 A CN202010857201 A CN 202010857201A CN 111959830 B CN111959830 B CN 111959830B
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- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
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Abstract
The invention provides a thermal control system and a thermal control method for a satellite high-precision optical load mounting platform, which comprise the following steps: the external environment thermal control module is configured to reduce the influence of an external environment on the temperature uniformity of the satellite high-precision optical load mounting platform body through an external heat flow shielding unit, a boundary temperature control unit and a mounting component heat insulation unit; and the platform body thermal control module is configured to uniform the temperature of the platform body thermal control module through the surface thermal insulation unit, the heating circuit arrangement unit and the PI closed-loop temperature control unit.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a thermal control system and method for a satellite high-precision optical load mounting platform.
Background
A scientific satellite is provided with three loads, the three loads are required to be viewed by the sun, the optical axis deviation is required to be less than 30', the optical axis parallelism is mainly influenced by the general assembly environment, the load installation mode (no gravity installation), the thermoelastic deformation and the momentum wheel micro-vibration disturbance, wherein the influence of the thermoelastic deformation of the load installation platform is an important ring, so that the temperature and gradient stability of the load installation platform are ensured, the thermoelastic deformation of the load installation platform is reduced, and the method is an important technical measure for ensuring the optical axis parallelism of the load.
The environmental temperature (the on-orbit control temperature of the load) is adjusted to be 22 ℃ in combination with the ground installation of the load, the decomposition is carried out according to the overall technical index, and the temperature requirement of the load installation platform is controlled to be 22 +/-5 ℃. The satellite orbit is a 720KM orbit height sun synchronous orbit, the attitude of the satellite is + X direction and is opposite to sun direction because the satellite needs to observe the sun at the moment, and the inner wheel flow in +/-Y direction in one orbit is influenced by earth infrared and albedo under the attitude of the satellite; therefore, the heat flow difference of the satellite in each direction is large, the load mounting platform is positioned outside a cabin in the + Z direction of the satellite and is completely exposed outside the cabin to be influenced by the external heat flow, and the temperature difference of each surface is large; on the other hand, the load mounting platform is large in size (1.6m x 0.8m), and the carbon fiber material with low elastic modulus is adopted as the material of the optical reference plate skin, the frame and the support rod in the aspect of structure, and the temperature uniformity of each part of the load mounting platform is difficult to control due to poor heat conduction performance of the carbon fiber, so that the requirement that the temperature of the load mounting platform is controlled within 22 +/-5 ℃ is difficult.
Disclosure of Invention
The invention aims to provide a thermal control system and a thermal control method for a high-precision optical load mounting platform of a satellite, which aim to solve the problem that the temperature uniformity of the platform is difficult to control due to large heat flow difference in each direction, large size of the load mounting platform and poor heat conduction of materials of the conventional satellite.
In order to solve the above technical problem, the present invention provides a thermal control system for a satellite high-precision optical load mounting platform, comprising:
the external environment thermal control module is configured to reduce the influence of an external environment on the temperature uniformity of the satellite high-precision optical load mounting platform body through an external heat flow shielding unit, a boundary temperature control unit and a mounting component heat insulation unit;
and the platform body thermal control module is configured to uniform the temperature of the platform body thermal control module through the surface thermal insulation unit, the heating circuit arrangement unit and the PI closed-loop temperature control unit.
Optionally, in the thermal control system for the satellite high-precision optical load mounting platform,
the satellite with the satellite high-precision optical load mounting platform is positioned in a solar synchronous orbit with the height of 720 KM;
the attitude of the satellite with the satellite high-precision optical load mounting platform is oriented to the sun in the + X direction;
the attitude of the satellite with the satellite high-precision optical load mounting platform is +/-Y-direction in-orbit wheel flow influenced by earth infrared and albedo;
the satellite high-precision optical load mounting platform is completely exposed out of a satellite plus Z-direction cabin;
the load comprises three loads and radiation plates thereof, and the single machine comprises a satellite sensitive radiation plate, a fiber optic gyroscope and a measurement and control antenna;
three loads are viewed from the sun in common, and the deviation of the optical axis is less than 30'.
Optionally, in the thermal control system for a satellite high-precision optical load mounting platform, the external heat flow shielding unit includes:
the cabin-sealing multilayer heat insulation assembly is configured to perform cabin-sealing coating on the load cabin body so as to reduce temperature fluctuation of the effective load caused by external thermal current change;
a sun visor disposed on the satellite capsule on one side oriented to the day;
the sun shield is an aluminum honeycomb sun shield with the thickness of 8 mm-12 mm;
and a glass fiber reinforced plastic heat insulation pad is arranged between the sun shield and the satellite platform.
Optionally, in the thermal control system for a satellite high-precision optical load mounting platform, the mounting component heat insulation unit includes:
the titanium alloy heat insulation supports are arranged at the top of the satellite platform cabin for heat insulation installation and support the satellite high-precision optical load installation platform;
and the stand-alone glass fiber reinforced plastic heat insulation pad is configured for heat insulation installation between a plurality of loads and a stand-alone and the satellite high-precision optical load installation platform so as to reduce thermal coupling between the plurality of loads and the stand-alone and the satellite high-precision optical load installation platform, and the thickness of the stand-alone glass fiber reinforced plastic heat insulation pad is 8-12 mm.
Optionally, in the thermal control system for a satellite high-precision optical load mounting platform, the boundary temperature control unit is configured to adopt active thermal control to enable target temperatures of the three loads and the fiber-optic gyroscope to be within a range of 22 ± 3 ℃, so as to ensure temperature uniformity of a mounting surface of the payload.
Optionally, in the thermal control system for a satellite high-precision optical load mounting platform, the surface heat insulation unit includes:
the load mounting plate multilayer heat insulation assembly is configured to cover the load mounting plate and reduce radiation heat leakage between the load mounting plate and the external heat flow shielding unit;
the load support rod multilayer heat insulation assembly is configured to cover the load support rod, and radiation heat leakage between the load support rod and the external heat flow shielding unit is reduced.
Optionally, in the thermal control system for a satellite high-precision optical load mounting platform, the heating circuit arrangement unit includes:
the load support rod heating loop is arranged on a plurality of load support rods which are parallel and level in the X direction and is used for actively heating and controlling the temperature of the load support rods;
load mounting plate heating circuit: the system is configured to actively heat and control the temperature of the load mounting plate according to the load and the layout of the single machine on the load mounting plate;
arranging four heating areas in two loads and a radiation plate mounting area of the plus Z side of the satellite, wherein each heating area is provided with a main heating loop and a standby heating loop;
arranging two heating areas in a load and radiation plate installation area on the Z side of the satellite, wherein each heating area is provided with a main heating loop and a standby heating loop;
arranging four heating areas in a satellite-Z side satellite sensitive installation area, wherein each heating area is provided with 1 heating loop;
1 heating loop is designed in the installation area of the sun shield, and 1 heating loop is designed in the installation area of the satellite sensitive radiation plate.
Optionally, in the thermal control system for a satellite high-precision optical load mounting platform, the PI closed-loop temperature control unit is configured to perform PI active closed-loop control on the load support rod heating circuit and the load mounting plate heating circuit through a computer, and the target temperature is 22 ℃.
Optionally, in the thermal control system for the satellite high-precision optical load mounting platform, the size of the satellite high-precision optical load mounting platform is 1.6m × 0.8m, and a carbon fiber material is used as a material for an optical reference plate skin, a frame and a support rod.
The invention also provides a thermal control system of the satellite high-precision optical load mounting platform, which comprises:
the external environment thermal control module reduces the influence of the external environment on the temperature uniformity of the satellite high-precision optical load mounting platform body through an external heat flow shielding unit, a boundary temperature control unit and a mounting component heat insulation unit;
the platform body thermal control module is used for homogenizing the temperature of the platform body thermal control module through the surface thermal insulation unit, the heating loop arrangement unit and the PI closed-loop temperature control unit.
In the thermal control system and the method for the satellite high-precision optical load mounting platform, the influence of an external environment on the temperature uniformity of a satellite high-precision optical load mounting platform body is reduced through an external heat flow shielding unit, a boundary temperature control unit and a mounting part heat insulation unit, the temperature of the thermal control system is uniform through a surface heat insulation unit, a heating loop arrangement unit and a PI closed-loop temperature control unit, the temperature uniformity control of the large-size load mounting platform is realized, the temperature uniformity of the load mounting platform can be controlled to be 22 +/-3 ℃, the thermoelastic deformation of the load mounting platform is matched with schemes such as a final assembly environment, a load mounting mode (no gravity mounting) and the like, and the requirements that three loads are viewed by the sun and the deviation of an optical axis is less than 30' are finally met; meanwhile, the method provides related technical reference for the ultra-precise and ultra-stable platform and the thermoelastic deformation control of related scientific satellites.
Drawings
FIG. 1 is a schematic diagram of a high-precision optical load mounting platform for a satellite according to an embodiment of the invention;
FIG. 2 is a schematic diagram of a thermal control system of a high-precision optical load mounting platform for a satellite according to an embodiment of the invention;
FIG. 3 is a schematic view of the + Z plane of a load mounting plate of a high-precision optical load mounting platform for a satellite according to an embodiment of the invention;
FIG. 4 is a schematic view of the load mounting plate-Z of the high-precision optical load mounting platform of the satellite according to one embodiment of the invention;
FIG. 5 is a diagram of the state inside the vacuum tank of the satellite and parallelism monitoring apparatus according to one embodiment of the invention;
FIG. 6 is a graph of temperature change during a thermal balance test of a support bar of an optical load mounting platform according to one embodiment of the present invention;
FIG. 7 is a graph of temperature change during a + Z side thermal balance test for an optical load mounting platform according to one embodiment of the present invention;
FIG. 8 is a graph of temperature change in a Z-side thermal balance test for an optical load mounting platform according to one embodiment of the present invention;
FIG. 9 shows the results of parallelism between the optical axes of the full-test periodic load according to an embodiment of the present invention;
shown in the figure: 10-star mine; 20-a measurement and control antenna; 30-a gyroscope; 40-optical load one; 50-optical loading two; 60-optical load three.
Detailed Description
The thermal control system and method for a high-precision optical load mounting platform of a satellite according to the present invention will be described in detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
The core idea of the invention is to provide a thermal control system and a thermal control method for a high-precision optical load mounting platform of a satellite, so as to solve the problem of difficult control of platform temperature uniformity caused by large heat flow difference in each direction, large size of the load mounting platform and poor heat conduction of materials of the conventional satellite.
In order to solve the problems of large heat flow difference in each direction of the satellite, large size of a load mounting platform and difficult control of platform temperature uniformity caused by poor heat conduction of materials, the invention provides a thermal control method for controlling the temperature uniformity of the load mounting platform, which meets the requirements that the temperature uniformity of the load mounting platform is controlled within 22 +/-5 ℃ during an on-orbit task, the thermal elastic deformation of the platform is controlled, and finally the requirements that three loads are viewed by the sun in common and the deviation of an optical axis is less than 30' are met.
In order to realize the thought, the invention provides a thermal control system and a thermal control method for a satellite high-precision optical load mounting platform, which comprises the following steps: the external environment thermal control module is configured to reduce the influence of an external environment on the temperature uniformity of the satellite high-precision optical load mounting platform body through an external heat flow shielding unit, a boundary temperature control unit and a mounting component heat insulation unit; and the platform body thermal control module is configured to uniform the temperature of the platform body thermal control module through the surface thermal insulation unit, the heating circuit arrangement unit and the PI closed-loop temperature control unit.
The present embodiment provides a thermal control system for a satellite high-precision optical load mounting platform, as shown in fig. 2, including: the external environment thermal control module is configured to reduce the influence of an external environment on the temperature uniformity of the satellite high-precision optical load mounting platform body through an external heat flow shielding unit, a boundary temperature control unit and a mounting component heat insulation unit; and the platform body thermal control module is configured to uniform the temperature of the platform body thermal control module through the surface thermal insulation unit, the heating circuit arrangement unit and the PI closed-loop temperature control unit.
In one embodiment of the invention, in the thermal control system of the satellite high-precision optical load mounting platform, as shown in fig. 1, the satellite with the satellite high-precision optical load mounting platform is located in a sun synchronous orbit with the height of 720 KM; the attitude of the satellite with the satellite high-precision optical load mounting platform is oriented to the sun in the + X direction; the attitude of the satellite with the satellite high-precision optical load mounting platform is +/-Y-direction in-orbit wheel flow influenced by earth infrared and albedo; the satellite high-precision optical load mounting platform is completely exposed out of a satellite plus Z-direction cabin; the load comprises three loads (an optical load I40, an optical load II 50 and an optical load III 60) and radiation plates thereof, and the single machine comprises a satellite sensor 10, a satellite sensor radiation plate, a fiber-optic gyroscope 30 and a measurement and control antenna 20; three loads are viewed from the sun in common, and the deviation of the optical axis is less than 30'.
In an embodiment of the present invention, in the thermal control system for a satellite high-precision optical load mounting platform, the external heat flow shielding unit includes: a capsule-sealing multilayer heat-insulating assembly S1, which is configured to seal and coat the load capsule body to reduce the temperature fluctuation of the effective load caused by external heat flow change; a sun visor S2 disposed on the side of the satellite pod oriented to the day; the sun shield is an aluminum honeycomb sun shield with the thickness of 8 mm-12 mm; and a glass fiber reinforced plastic heat insulation pad is arranged between the sun shield and the satellite platform.
In one embodiment of the present invention, in the thermal control system for a high-precision optical load mounting platform of a satellite, the mounting component heat insulation unit comprises: the titanium alloy heat insulation supports S3 are arranged at the top of the satellite platform cabin for heat insulation installation and support the satellite high-precision optical load installation platform; and the stand-alone glass fiber reinforced plastic heat insulation pad S4 is configured to be used for heat insulation installation between the plurality of loads and the stand-alone and the satellite high-precision optical load installation platform so as to reduce thermal coupling between the plurality of loads and the stand-alone and the satellite high-precision optical load installation platform, and the thickness of the stand-alone glass fiber reinforced plastic heat insulation pad is 8-12 mm.
In an embodiment of the invention, in the satellite high-precision optical load mounting platform thermal control system, the boundary temperature control unit (load and single-machine temperature control S5) is configured to adopt active thermal control to make target temperatures of three loads and a fiber-optic gyroscope within a range of 22 ± 3 ℃ so as to ensure temperature uniformity of a payload mounting surface.
In one embodiment of the present invention, in the thermal control system for a satellite high-precision optical load mounting platform, the surface thermal insulation unit comprises: a load mounting plate multilayer insulation assembly S6 configured to encase the load mounting plate, reducing radiant heat leakage between the load mounting plate and the external heat flow shield unit; and the load support bar multi-layer heat insulation assembly S6 is configured to wrap the load support bar and reduce radiation heat leakage between the load support bar and the external heat flow shielding unit.
As shown in fig. 3 and 4, in the thermal control system for a satellite high-precision optical load mounting platform, the heating circuit arrangement unit includes: the load support rod heating loop S7 is arranged on a plurality of load support rods with the same X direction and is used for actively heating and controlling the temperature of the load support rods; load mount plate heating circuit S8: the system is configured to actively heat and control the temperature of the load mounting plate according to the load and the layout of the single machine on the load mounting plate; arranging four heating areas in two loads and a radiation plate mounting area of the plus Z side of the satellite, wherein each heating area is provided with a main heating loop and a standby heating loop; arranging two heating areas in a load and radiation plate installation area on the Z side of the satellite, wherein each heating area is provided with a main heating loop and a standby heating loop; arranging four heating areas in a satellite-Z side satellite sensitive installation area, wherein each heating area is provided with 1 heating loop; 1 heating loop is designed in the installation area of the sun shield, and 1 heating loop is designed in the installation area of the satellite sensitive radiation plate.
In an embodiment of the present invention, in the thermal control system for a satellite high-precision optical load mounting platform, the PI closed-loop temperature control unit S9 is configured to perform PI active closed-loop control on the load supporting rod heating circuit and the load mounting plate heating circuit through a computer, and the target temperature is 22 ℃.
In one embodiment of the invention, in the thermal control system of the satellite high-precision optical load mounting platform, the size of the satellite high-precision optical load mounting platform is 1.6m by 0.8m, and carbon fiber materials are used as materials of an optical reference plate skin, a frame and a support rod.
This embodiment still provides a satellite high accuracy optics load mounting platform thermal control system, includes: the external environment thermal control module reduces the influence of the external environment on the temperature uniformity of the satellite high-precision optical load mounting platform body through an external heat flow shielding unit, a boundary temperature control unit and a mounting component heat insulation unit; the platform body thermal control module is used for homogenizing the temperature of the platform body thermal control module through the surface thermal insulation unit, the heating loop arrangement unit and the PI closed-loop temperature control unit.
In the thermal control system and the method for the satellite high-precision optical load mounting platform, the influence of an external environment on the temperature uniformity of a satellite high-precision optical load mounting platform body is reduced through an external heat flow shielding unit, a boundary temperature control unit and a mounting part heat insulation unit, the temperature of the thermal control system is uniform through a surface heat insulation unit, a heating loop arrangement unit and a PI closed-loop temperature control unit, the temperature uniformity control of the large-size load mounting platform is realized, the temperature uniformity of the load mounting platform can be controlled to be 22 +/-3 ℃, the thermoelastic deformation of the load mounting platform is matched with schemes such as a final assembly environment, a load mounting mode (no gravity mounting) and the like, and the requirements that three loads are viewed by the sun and the deviation of an optical axis is less than 30' are finally met; meanwhile, the method provides related technical reference for the ultra-precise and ultra-stable platform and the thermoelastic deformation control of related scientific satellites.
The thermal control technology of the load mounting platform can be divided into an external environment thermal control technology and a platform body thermal control technology, wherein the external environment thermal control technology is used for reducing the influence of an external environment on the temperature uniformity of the platform through external heat flow shielding, boundary temperature control and mounting part heat insulation, and the platform body thermal control technology is used for ensuring the temperature uniformity of a flat remote place through surface heat insulation, heating circuit arrangement and PI closed-loop temperature control.
Cabin-closing multilayer insulation assembly S1: because the load cabin is not provided with four side cabin sealing plates, in order to reduce the influence of external heat flow on the heat radiation of the load mounting platform, the periphery of the load cabin is coated in a cabin sealing mode by adopting 15 layers of multilayer heat insulation assemblies, so that the fluctuation of the effective load temperature caused by the change of the external heat flow is reduced;
sun visor S2: the sun of the satellite and the X are oriented to the sun, in order to reduce the influence of the solar radiation heat flow on the + X side on the temperature of the platform, a 10mm thick aluminum honeycomb sun visor is designed on the + X side of the platform, the sun visor and the platform are installed in a heat insulation mode through a 30mm glass fiber reinforced plastic heat insulation pad, and 15 layers of heat insulation assemblies are coated on the back face of the sun visor to reduce heat leakage of the sun visor on the installation platform;
titanium alloy heat insulation support S3: the load mounting platform is mounted at the top of the satellite platform cabin, the temperature of the platform cabin fluctuates at 10-30 ℃, and in order to reduce the influence of the temperature fluctuation of the platform cabin and ensure the strength and rigidity of the support, four 100mm high-titanium alloy supports are adopted for heat insulation mounting;
single machine fiberglass insulation S4: as shown in fig. 1, the load mounting platform is provided with three loads and radiation plates thereof, a star sensor and a star sensor radiation plate, a fiber optic gyroscope and a measurement and control antenna, and in order to reduce thermal coupling between each single machine and the load mounting platform, each load and the load mounting platform are installed in a heat insulation way by adopting a glass fiber reinforced plastic heat insulation pad with the thickness of 10 mm;
load and stand-alone temperature control S5: in order to reduce the influence of the load and a single machine on the temperature of the load and the single machine at the mounting position of the load mounting platform, the load and the single machine adopt an active thermal control design, and the target temperatures of the three effective loads and the fiber-optic gyroscope are controlled within 22 +/-3 ℃ so as to ensure the temperature uniformity of the mounting surface of the effective loads;
mounting plate and brace bar multi-layer insulation assembly S6: on the basis of insulating heat to external heat flow and star radiation through the cabin-sealing multilayer and the sun shield, the load mounting plate and the support rod are further coated with 15 layers of multilayer heat-insulating assemblies, so that the radiation heat leakage of the load mounting plate and the support rod, the cabin-sealing multilayer and the sun shield is reduced, and the temperature uniformity control difficulty of a load mounting platform is reduced;
strut heating circuit arrangement S7: in order to ensure the temperature uniformity of the supporting rods of the load mounting platform, active heating loops are arranged on the supporting rods, the temperature of the supporting rods is gradually reduced along the X direction due to the fact that the supporting rods face the sun, the heating loops are arranged in a mode that 1 heating loop is arranged on a rod frame which is parallel and level to the X direction, and 7 active heating loops are used for conducting active heating temperature control;
mounting plate heating circuit arrangement S8: in order to ensure the temperature uniformity of the load mounting plate, heating loops are arranged according to the arrangement of loads and a single machine on the load mounting plate, four heating areas are arranged on the + Z side for two load and two load radiation plate (low temperature) mounting areas, 1 main heating area and 2 heating loops are arranged on each heating area, six heating areas and 8 heating loops are arranged on the-Z side for one load and satellite sensitive (low temperature) mounting area, and 1 heating loop is respectively designed on the sun shield and satellite sensitive radiation plate mounting areas to count 18 heating loops;
active heating loop PI closed loop temperature control S9: and (3) arranging heating loops on the support rods and the mounting plate through a computer to perform PI active closed-loop control, wherein the target temperature is 22 ℃.
Under the complex on-orbit environment, a thermal control method for temperature uniformity is provided for a large-size load mounting platform, the temperature uniformity can be within 22 +/-5 ℃, the thermoelastic deformation of the platform is controlled, and finally the requirements that three loads are viewed by the sun in common and the deviation of an optical axis is less than 30' are met.
15 layers of multilayer heat insulation assemblies are arranged on the periphery of the load mounting platform to isolate the influence of external heat flow; the sun shield is arranged in the sun-facing surface and the X direction, so that the influence of solar radiation heat flow of the sun-facing surface is reduced; the satellite platform and the high titanium alloy support with the height of 100mm are installed in a heat insulation mode, and the influence of temperature fluctuation of the platform cabin is reduced; the single machine and the radiation plate of the installation platform are installed by adopting 10mm glass fiber reinforced plastic heat insulation, so that the thermal coupling between the single machine and the radiation plate and the installation platform is reduced; the three loads of the mounting platform and the fiber-optic gyroscope are actively heated, and the temperature is controlled within 22 +/-3 ℃; the surfaces of the mounting plate and the support rod are provided with 15 layers of multilayer heat insulation assemblies, so that the radiation heat leakage of the load mounting plate, the support rod, the cabin sealing multilayer and the sun shield is reduced; 1 heating loop is arranged on the parallel rod frame of the stay rod along the X direction, and 7 active heating loops are arranged in total to actively heat and control the temperature of the stay rod; arranging heating loops according to the layout of loads and a single machine on a load mounting plate, arranging four heating areas for two load and two load radiation plate (low-temperature) mounting areas on the + Z side, arranging 8 heating loops on the main and standby, arranging six heating areas for one load and satellite-sensitive (low-temperature) mounting area on the-Z side, arranging 8 heating loops on the six heating areas, and simultaneously designing 1 heating loop in each of the sun shield and satellite-sensitive radiation plate mounting areas to count 18 heating loops; and (3) arranging heating loops on the support rods and the mounting plate through a computer to perform PI active closed-loop control, wherein the target temperature is 22 ℃.
In order to verify the effectiveness of the thermal control scheme, the load mounting platform performs a thermal balance test in a vacuum environment along with the whole satellite, a parallelism detection device is mounted in a vacuum tank, the parallelism of the optical axis of the load is monitored in real time in the test process, and the state in the tank is as shown in fig. 5.
As shown in fig. 6 to 8, in the thermal control scheme, the temperature of the support rod of the optical load mounting platform is controlled to be 19.5 ℃ to 22.5 ℃ under the high-low temperature working condition of the thermal balance test, the temperature difference can be controlled to be within 3 ℃, and the temperature fluctuation of the temperature measuring point is controlled to be within 0.4 ℃; the temperature of the platform plus Z side is between 19.1 and 22.6 ℃, the temperature difference can be controlled within 3.5 ℃, and the temperature fluctuation of a temperature measuring point is controlled within 0.5 ℃; the temperature of the platform-Z side is between 20.1 and 22.6 ℃, the temperature difference can be controlled within 2.5 ℃, the temperature fluctuation of a temperature measuring point is controlled within 0.5 ℃, and the temperature of the side load mounting surface is between 21.0 and 22.6 ℃. Under the thermal control scheme, the load mounting platform is subjected to compensation heating through PI temperature control, and the high-temperature working condition is compensated by 38W; and the low-temperature working condition is compensated by 41W. The test result shows that the temperature uniformity of all parts of the load mounting platform can be controlled within 22 +/-3 ℃.
Meanwhile, in the whole test process, the parallelism of the three load optical axes is monitored in real time through the parallelism monitoring device, the load single machine is replaced by the reference prism of the load single machine in the test process, the optical axes of the three loads are respectively represented by No. 1, No. 2 and No. 3 prisms, and the test result is shown in FIG. 9.
As can be seen from FIG. 9, the parallelism among the optical axes of the three payloads fluctuates with time in the whole thermal balance test process, the fluctuation interval is basically within the range of +/-5 "of the working condition mean value, the maximum fluctuation amount is less than 15", and the change of the parallelism among the optical axes of the payloads in the whole test process is controllable.
In summary, the above embodiments have described in detail various configurations of the thermal control system and method for a high-precision optical load mounting platform of a satellite, and it is understood that the present invention includes, but is not limited to, the configurations listed in the above embodiments, and any modifications based on the configurations provided in the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (7)
1. The utility model provides a satellite high accuracy optics load mounting platform thermal control system which characterized in that includes:
the satellite is provided with three loads, the three loads are viewed from the sun, the optical axis deviation requirement is less than 30', and the on-orbit control temperature of the loads is 22 ℃;
the external environment thermal control module is configured to reduce the influence of an external environment on the temperature uniformity of the satellite high-precision optical load mounting platform body through an external heat flow shielding unit, a boundary temperature control unit and a mounting component heat insulation unit;
a platform body thermal control module configured to uniformize its own temperature by a surface heat-insulating and heat-preserving unit, a heating circuit arrangement unit, and a PI closed-loop temperature control unit;
the attitude of the satellite with the satellite high-precision optical load mounting platform is oriented to the sun in the + X direction;
the attitude of the satellite with the satellite high-precision optical load mounting platform is +/-Y-direction in-orbit wheel flow influenced by earth infrared and albedo;
the satellite high-precision optical load mounting platform is completely exposed out of a satellite plus Z-direction cabin;
the load comprises three loads and radiation plates thereof, and the single machine comprises a satellite sensitive radiation plate, a fiber optic gyroscope and a measurement and control antenna;
the external heat flow shielding unit includes:
the cabin-sealing multilayer heat insulation assembly is configured to perform cabin-sealing coating on the load cabin body so as to reduce temperature fluctuation of the effective load caused by external thermal current change;
a sun visor disposed on the satellite capsule on one side oriented to the day;
the mounting member heat insulating unit includes:
the titanium alloy heat insulation supports are arranged at the top of the satellite platform cabin for heat insulation installation and support the satellite high-precision optical load installation platform;
a stand-alone fiberglass thermal insulation blanket configured for thermal insulation installation between a plurality of loads and a stand-alone and the satellite high-precision optical load mounting platform;
the surface heat insulation and preservation unit comprises:
the load mounting plate multilayer heat insulation assembly is configured to cover the load mounting plate and reduce radiation heat leakage between the load mounting plate and the external heat flow shielding unit;
the load supporting rod multilayer heat insulation assembly is configured to cover the load supporting rod and reduce radiation heat leakage between the load supporting rod and the external heat flow shielding unit;
the heating circuit arrangement unit includes:
the load support rod heating loop is arranged on a plurality of load support rods which are parallel and level in the X direction and is used for actively heating and controlling the temperature of the load support rods;
load mounting plate heating circuit: the system is configured to actively heat and control the temperature of the load mounting plate according to the load and the layout of the single machine on the load mounting plate;
arranging four heating areas in two loads and a radiation plate mounting area of the plus Z side of the satellite, wherein each heating area is provided with a main heating loop and a standby heating loop;
arranging two heating areas in a load and radiation plate installation area on the Z side of the satellite, wherein each heating area is provided with a main heating loop and a standby heating loop;
arranging four heating areas in a satellite-Z side satellite sensitive installation area, wherein each heating area is provided with 1 heating loop;
1 heating loop is designed in the installation area of the sun shield, and 1 heating loop is designed in the installation area of the satellite sensitive radiation plate.
2. The satellite high-precision optical load mount platform thermal control system of claim 1,
the satellite with the satellite high-precision optical load mounting platform is positioned in a solar synchronous orbit with the height of 720 KM;
three loads are viewed from the sun in common, and the deviation of the optical axis is less than 30'.
3. The satellite high-precision optical load mount platform thermal control system of claim 2,
the sun shield is an aluminum honeycomb sun shield with the thickness of 8 mm-12 mm;
and a glass fiber reinforced plastic heat insulation pad is arranged between the sun shield and the satellite platform.
4. The satellite high-precision optical load mount platform thermal control system of claim 3,
the single-machine glass fiber reinforced plastic heat insulation pad reduces a plurality of loads and thermal coupling between a single machine and the satellite high-precision optical load mounting platform, and the thickness of the single-machine glass fiber reinforced plastic heat insulation pad is 8-12 mm.
5. The satellite high-precision optical load mount platform thermal control system of claim 3, wherein the boundary temperature control unit is configured to employ active thermal control to maintain target temperatures of the three loads and the fiber optic gyroscope within a range of 22 ± 3 ℃ to ensure temperature uniformity of the payload mounting surface.
6. The satellite high-precision optical load mount platform thermal control system of claim 1, wherein the PI closed-loop temperature control unit is configured to perform PI active closed-loop control on the load support bar heating circuit and the load mount plate heating circuit by a computer, with a target temperature of 22 ℃.
7. The satellite high-precision optical load mount platform thermal control system of claim 1, wherein the satellite high-precision optical load mount platform has dimensions of 1.6m x 0.8m, and carbon fiber materials are used as the material for the optical reference plate skin, the frame and the support rods.
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