CN114655471A - Thermal control system and method for spacecraft extravehicular equipment running on low-inclination-angle track - Google Patents
Thermal control system and method for spacecraft extravehicular equipment running on low-inclination-angle track Download PDFInfo
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- CN114655471A CN114655471A CN202210196465.3A CN202210196465A CN114655471A CN 114655471 A CN114655471 A CN 114655471A CN 202210196465 A CN202210196465 A CN 202210196465A CN 114655471 A CN114655471 A CN 114655471A
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- 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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Abstract
The invention provides a thermal control system of equipment outside a spacecraft cabin running on a low-inclination-angle track, which comprises a platform cabin plate, a load host and a load antenna, wherein the load host is arranged on the platform cabin plate, the load antenna is arranged on the load host, the surface of the load antenna is sprayed with heat dissipation white paint, the side surface of the load host is sprayed with heat dissipation white paint, one half of the top surface of the load host is sprayed with white paint, the other half of the top surface of the load host is coated with a heat insulation multilayer coating, and an active temperature control heating loop for active thermal control is arranged on the load host. The invention also provides a thermal control method of the spacecraft extra-cabin equipment running on the low-inclination-angle track. The invention has the beneficial effects that: on the premise of not increasing the weight of the satellite, a passive thermal control and active thermal control combined mode is adopted, and the on-orbit autonomous control function of satellite affair software on the satellite is fully utilized to realize the temperature fluctuation control function.
Description
Technical Field
The invention relates to a spacecraft, in particular to a thermal control system and a thermal control method for spacecraft equipment outside a cabin running on a low-inclination orbit.
Background
The method is characterized in that load equipment is installed outside a spacecraft cabin and is commonly installed on a spacecraft, the load equipment outside the spacecraft cabin and a spacecraft platform are installed in a heat insulation mode in a conventional design, the influence of the temperature fluctuation of the platform on the load is reduced, independent temperature control is carried out on the load equipment outside the spacecraft cabin, and generally a measure that a multilayer heat insulation assembly is combined with heat dissipation white paint and temperature control is carried out by an electric heating loop is adopted to solve the problem.
For a general satellite running in a sun synchronous orbit, external heat flow is stable, and a conventional thermal control design method comprises the following steps: and the load equipment is controlled to be at a lower temperature level by using the electric heating loop, and the temperature level of the equipment is controlled to be within a required temperature range.
For a general satellite running in a low-inclination orbit, the fluctuation of external heat flow on each side surface of a spacecraft is large, the adopted thermal control design method is similar to the extravehicular load on a sun synchronous orbit, the fluctuation of the external heat flow is large, and the illumination period and the ground shadow period are alternated, so that more energy is needed for thermal control in the method, and a large solar cell array is generally designed for a power supply assembly on the satellite to meet the power consumption requirement of load thermal control. Or other active thermal control devices, such as a radiation-type active thermal control device, are adopted to change the radiation heat dissipation capacity of the star body by changing the surface emissivity at the heat dissipation surface: the active thermal control device is provided with a thermal control shutter, a thermal control rotating disc and the like, and not only makes a thermal control assembly become complex, but also increases the weight of the whole satellite.
At present, most of extra-cabin loads are applied to spacecrafts with solar synchronous orbits, the problem of large fluctuation of external heat flow does not exist, and the extra-cabin loads are installed in a heat insulation mode and independently controlled with a platform, so that the temperature level and fluctuation can be well controlled, but the power consumption required to be consumed by thermal control is more.
Along with the commercial batch production development of the satellite, the integration level of the satellite is higher and higher, the size of the satellite is smaller and smaller, the energy density is higher, the energy of the satellite is designed according to the requirement, the surplus on the satellite is small, the size of the satellite is larger due to the heat insulation installation, and more energy is consumed due to the independent temperature control. The method is still suitable for controlling the temperature and fluctuation of the extravehicular load of the spacecraft running on the sun synchronous orbit, the fluctuation of the heat flow outside the low-inclination orbit is large, and full light and ground shadow areas alternately appear all the year round, so that the energy consumption required by the method is overlarge. Similarly, the active thermal control device not only makes the thermal control assembly become complex, but also increases the weight of the whole satellite, and is not suitable for commercial satellites. Therefore, a new method for realizing the temperature fluctuation control function by fully utilizing the on-orbit autonomous control function of the satellite affair software on the satellite on the premise of not increasing the weight of the satellite is needed.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a thermal control system and a thermal control method for spacecraft equipment outside a cabin running on a low-inclination-angle track.
The invention provides a thermal control system of spacecraft equipment outside a cabin running on a low-inclination-angle track, which comprises a platform cabin plate, a load host and a load antenna, wherein the load host is arranged on the platform cabin plate, the load antenna is arranged on the load host, the surface of the load antenna is sprayed with heat dissipation white paint, the side surface of the load host is sprayed with the heat dissipation white paint, one half of the top surface of the load host is sprayed with the white paint, the other half of the top surface of the load host is coated with a heat insulation multilayer coating, and an active temperature control heating loop for active thermal control is arranged on the load host.
As a further improvement of the invention, the load antenna is overhead on the load host machine through an aluminum alloy stud.
As a further improvement of the invention, the four side surfaces of the load main machine are sprayed with heat dissipation white paint.
The invention also provides a thermal control method of the spacecraft extra-cabin equipment running on the low-inclination-angle orbit, and based on the thermal control system of the spacecraft extra-cabin equipment running on the low-inclination-angle orbit, the following processes are carried out: the temperature control point is positioned on the installation plane of the load host and the platform deck, the active temperature control heating circuit is controlled through the housekeeping software, the active temperature control heating circuit is used for carrying out real-time dynamic closed-loop temperature control on the load host according to the temperature of the temperature control point, and the temperature fluctuation of the temperature control point is controlled within a required range.
As a further improvement of the invention, the active temperature control heating loop automatically modifies the loop temperature control interval to be [ Tmax-5 and Tmax-1] by the housekeeping software according to the maximum value Tmax in the temperature control point setting until the temperature tends to be stable.
As a further improvement of the invention, the active temperature control heating loop is not controlled in a closed loop mode by a fixed temperature control interval, and according to the maximum value Tmax within 2 hours of the temperature control point, the star software autonomously modifies the loop temperature control interval to be [ Tmax-5, Tmax-1] until the temperature tends to be stable so as to meet the requirement that the temperature fluctuation within 48 hours is not more than +/-3 ℃.
As a further improvement of the invention, for the low-inclination orbit, when the beta angle of the spacecraft is larger, the star is fully illuminated, the temperature fluctuation of the temperature control point is less than +/-3 ℃, and active temperature control is not needed; when the beta angle of the spacecraft is small, the illumination and the ground shadow of each orbit are alternated, the temperature fluctuation of equipment outside a satellite on board is large, the temperature fluctuation of a temperature control point is larger than +/-3 ℃, the autonomous closed-loop temperature control of software is needed, the period of a satellite orbit is 105min, the satellite service software takes 2h as one period, the maximum temperature Tmax in the period is searched, the temperature control interval of a loop is autonomously modified to be [ Tmax-5 and Tmax-1], namely when the temperature is lower than Tmax-5, the active temperature control heating loop is started, and the lowest temperature in the period is higher than that in the last period; searching for the Tmax within 2h before the satellite is subjected to instant search, continuously updating the temperature control range of the temperature control interval by the satellite software, rapidly increasing the temperature of the temperature control point after the satellite leaves the terrestrial shadow, disconnecting the heating loop when the Tmax-1 is reached, possibly continuously increasing the temperature of the temperature control point due to the action of heat flow outside the illumination period, and finally keeping the temperature of the temperature control point stable due to negligible change of heat flow outside the satellite surface orbit within a few days in a short period, wherein the temperature control is performed for a plurality of periods of 2h, the final fluctuation is not more than 4 ℃, the requirement of being less than or equal to +/-3 ℃ within 48 hours is met, and the temperature control threshold value of the heating loop is modified in real time according to the Tmax, so that the heat control energy consumption is minimum, and the control requirement of temperature fluctuation is realized.
As a further improvement of the invention, the temperature requirements of the temperature control points are as follows: the working temperature range is required to be-15 to +45 ℃, and the temperature fluctuation is required to be not more than +/-3 ℃ within 48 hours.
The invention has the beneficial effects that: by the scheme, on the premise of not increasing the weight of the satellite body, the on-orbit autonomous control function of satellite software on the satellite is fully utilized by adopting a mode of combining passive thermal control and active thermal control to realize the temperature fluctuation control function.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other solutions can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic diagram of a thermal control system for an aerospace vehicle extra-cabin device operating in a low-pitch orbit, according to the invention.
FIG. 2 is a diagram of the simulation results of the temperature control algorithm for the thermal control method of the spacecraft equipment outside the cabin operating in a low-inclination orbit in accordance with the present invention.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The invention is further described with reference to the following description and embodiments in conjunction with the accompanying drawings.
As shown in fig. 1, a thermal control system of spacecraft equipment outside a cabin running in a low-inclination orbit is used for controlling temperature fluctuation of load equipment outside a satellite cabin with large external heat flow change, and mainly comprises a platform cabin plate 1, a load host 2 and a load antenna 3.
The contact relation in the load and the installation mode between the load and the platform are not controlled by the thermal control of the platform: the load antenna 3 is directly installed with the load host machine 2 through 8 long aluminum alloy studs, and the load antenna 3 is in a white paint spraying state.
The load host 2 has requirements for platform thermal control: the working temperature range of the installation cabin plate is required to be-15 to +45 ℃, and the temperature fluctuation is required to be not more than +/-3 ℃ within 48 hours. The temperature fluctuation of the antenna is large due to large heat flow fluctuation outside the track, and the temperature fluctuation of the load host is large in a radiation and heat conduction mode, so that the temperature fluctuation of the installation cabin plate is large finally.
A thermal control method for equipment outside a spacecraft cabin running on a low-inclination-angle track comprises the following steps of firstly, selecting a proper heat dissipation surface and a heat insulation multilayer coating to control the temperature of the equipment within an index range, designing four side surfaces of a load host machine 2 to be in a heat dissipation white paint spraying state, and setting half of the top surface to be in a white paint spraying state and half of the top surface to be in a coating multilayer state; a novel temperature control algorithm is injected on the housekeeping software, and the active temperature control heating loop is used for carrying out real-time dynamic closed-loop temperature control on the equipment according to the temperature of the equipment, so that the temperature fluctuation of the equipment is controlled within a required range.
As shown in fig. 2, based on passive thermal control, an active thermal control technique is used, and the active thermal control technique adopts a novel dynamic closed-loop temperature control algorithm: the heating loop is not controlled in a closed loop mode in a fixed temperature control interval, the star software automatically modifies the loop temperature control interval to be [ Tmax-5 and Tmax-1] according to the maximum Tmax within 2 hours of the temperature control point until the temperature tends to be stable, and the requirement that the temperature fluctuation is not more than +/-3 ℃ within 48 hours is met.
Passive thermal control: through selecting suitable cooling surface, 4 side whitewash of equipment, the top surface cladding is half multilayer, can assist the heat dissipation, can reduce the heat radiation between load host computer and the antenna again, weakens the influence of antenna to load host computer temperature fluctuation.
Active thermal control: the installation deck is temperature controlled by a dynamic closed loop temperature control algorithm using a heating circuit. And the index requirement of temperature fluctuation is realized.
The active thermal control is implemented as follows: for low-inclination orbits, when the beta angle of the spacecraft is larger, the stars are fully illuminated, the temperature fluctuation of the platform cabin plate is less than +/-3 ℃, and active temperature control is not needed; when the beta angle of the spacecraft is small, the illumination and the ground shadow of each orbit are alternated, the temperature fluctuation of equipment outside a satellite on the satellite is large, the temperature fluctuation of a cabin plate is larger than +/-3 ℃, the autonomous closed-loop temperature control of software is needed, the satellite orbit period is 105min, the satellite software takes 2h as a period, the maximum temperature Tmax in the period is searched, the temperature control interval of a loop is autonomously modified to be [ Tmax-5 and Tmax-1], namely when the temperature is lower than Tmax-5, the cabin plate heating loop is started, and the lowest temperature in the period is higher than that in the last period; searching the Tmax within the previous 2h immediately, and continuously updating the temperature control range of the temperature control interval by the housekeeping software. When the satellite leaves the terrestrial shadow period, the temperature of the temperature control point of the cabin plate is rapidly increased, the heating loop is disconnected when Tmax-1 is reached, and the temperature of the cabin plate may continue to increase due to the action of heat flow outside the illumination period. Because the change of heat flow outside the star surface orbit can be ignored within a short period of several days, the temperature of the cabin plate finally tends to be stable after temperature control for several 2h periods, the final fluctuation is not more than 4 ℃, and the requirement of being less than or equal to +/-3 ℃ within 48 hours is met. The temperature control threshold value of the heating loop is modified in real time according to the Tmax, so that the consumption of thermal control energy is minimum, and the control requirement of temperature fluctuation is met.
The invention provides a thermal control system and a thermal control method for spacecraft equipment outside a cabin running on a low-inclination-angle track, which are used for controlling the temperature of the equipment outside the cabin by combining passive thermal control measures (thermal control white paint and coating multiple layers of thermal insulation materials) and active thermal control measures (an electric heating loop) in a novel dynamic closed-loop temperature control algorithm mode, and controlling the temperature range and temperature fluctuation of the equipment within an allowable range.
The invention provides a thermal control system and a thermal control method for equipment outside a spacecraft cabin running on a low-inclination orbit, which can actively control the temperature of a mounting surface cabin plate in real time by using a new dynamic closed-loop thermal control algorithm through a conventional thermal control measure and a satellite software control heating circuit under the condition that the contact relation between the inside and the outside of a load cannot be changed and on the premise that an additional thermal control measure is not added, and successfully solve the problems of the temperature index and the temperature fluctuation requirement of the mounting surface cabin plate of the external load of a satellite cabin with large external thermal current change by using the minimum energy consumption.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (8)
1. A thermal control system of spacecraft extravehicular equipment operating on a low-inclination track is characterized in that: the heat dissipation white paint is sprayed on the surface of the load antenna, one half of the top surface of the load host is sprayed with the white paint, the other half of the top surface of the load host is coated with the heat insulation multilayer coating, and the load host is provided with an active temperature control heating loop for active thermal control.
2. The thermal control system for spacecraft extra-cabin equipment operating on low-inclination orbits of claim 1, further comprising: the load antenna is overhead on the load host machine through an aluminum alloy stud.
3. The thermal control system for spacecraft extra-cabin equipment operating on low-inclination orbits of claim 1, further comprising: and heat dissipation white paint is sprayed on four side surfaces of the load main machine.
4. A thermal control method for spacecraft equipment outside a cabin running on a low-inclination track is characterized by comprising the following steps: based on the thermal control system of the spacecraft equipment outside the cabin operating on low-inclination orbit of any one of claims 1 to 3, the following process is carried out: the temperature control point is positioned on the installation plane of the load host and the platform deck, the active temperature control heating circuit is controlled through the housekeeping software, the active temperature control heating circuit is used for carrying out real-time dynamic closed-loop temperature control on the load host according to the temperature of the temperature control point, and the temperature fluctuation of the temperature control point is controlled within a required range.
5. The method of claim 4 for thermal control of an extravehicular device of an aircraft operating on a low-pitch orbit, comprising: and the active temperature control heating loop automatically modifies the loop temperature control interval to be [ Tmax-5, Tmax-1] by the housekeeping software according to the maximum value Tmax in the temperature control point setting until the temperature tends to be stable.
6. The method of claim 5 for thermal control of an aerospace vehicle extravehicular device operating on a low-rake track, wherein: the active temperature control heating loop is not controlled in a closed loop mode in a fixed temperature control interval, and the star software automatically modifies the loop temperature control interval to be [ Tmax-5 and Tmax-1] according to the maximum Tmax within 2 hours of the temperature control point until the temperature tends to be stable so as to meet the requirement that the temperature fluctuation is not more than +/-3 ℃ within 48 hours.
7. The method of claim 6, wherein the method comprises: for low-inclination orbits, when the beta angle of the spacecraft is larger, the star body is fully illuminated, the temperature fluctuation of the temperature control point is less than +/-3 ℃, and active temperature control is not needed; when the beta angle of the spacecraft is small, the illumination and the ground shadow of each orbit are alternated, the temperature fluctuation of equipment outside a satellite on board is large, the temperature fluctuation of a temperature control point is larger than +/-3 ℃, the autonomous closed-loop temperature control of software is needed, the period of a satellite orbit is 105min, the satellite service software takes 2h as one period, the maximum temperature Tmax in the period is searched, the temperature control interval of a loop is autonomously modified to be [ Tmax-5 and Tmax-1], namely when the temperature is lower than Tmax-5, the active temperature control heating loop is started, and the lowest temperature in the period is higher than that in the last period; searching for the Tmax within 2h before instant search, continuously updating the temperature control range of the temperature control interval by the satellite software, rapidly increasing the temperature of the temperature control point after the satellite leaves the terrestrial shadow, disconnecting the heating loop when the Tmax-1 is reached, and possibly continuously increasing the temperature of the temperature control point due to the action of heat flow outside the illumination period, wherein the temperature of the temperature control point is controlled through a plurality of cycles of 2h because the change of the heat flow outside the satellite surface orbit can be ignored within a short period of several days, the temperature of the final temperature control point tends to be stable, the final fluctuation is not more than 4 ℃, the requirement of being less than or equal to +/-3 ℃ within 48 hours is met, and the temperature control threshold value of the heating loop is modified in real time according to the Tmax, so that the consumption of thermal control energy is minimum, and the control requirement of temperature fluctuation is realized.
8. The method of claim 4 for thermal control of an extravehicular device of an aircraft operating on a low-pitch orbit, comprising: the temperature requirements of the temperature control points are as follows: the working temperature range is required to be-15 to +45 ℃, and the temperature fluctuation is required to be not more than +/-3 ℃ within 48 hours.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210196465.3A CN114655471A (en) | 2022-03-01 | 2022-03-01 | Thermal control system and method for spacecraft extravehicular equipment running on low-inclination-angle track |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210196465.3A CN114655471A (en) | 2022-03-01 | 2022-03-01 | Thermal control system and method for spacecraft extravehicular equipment running on low-inclination-angle track |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115520410A (en) * | 2022-08-19 | 2022-12-27 | 中国科学院空间应用工程与技术中心 | Thermal control device and spacecraft laser time-frequency transmission load thermal control system |
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2022
- 2022-03-01 CN CN202210196465.3A patent/CN114655471A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115520410A (en) * | 2022-08-19 | 2022-12-27 | 中国科学院空间应用工程与技术中心 | Thermal control device and spacecraft laser time-frequency transmission load thermal control system |
| CN115520410B (en) * | 2022-08-19 | 2023-08-08 | 中国科学院空间应用工程与技术中心 | Spacecraft laser time-frequency transfer load thermal control system |
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