CN112265653A - Spacecraft autonomous thermal control method based on power balance - Google Patents
Spacecraft autonomous thermal control method based on power balance Download PDFInfo
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- CN112265653A CN112265653A CN202011068753.8A CN202011068753A CN112265653A CN 112265653 A CN112265653 A CN 112265653A CN 202011068753 A CN202011068753 A CN 202011068753A CN 112265653 A CN112265653 A CN 112265653A
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- 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
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Abstract
The invention relates to a spacecraft autonomous thermal control method based on power balance, which comprises the following steps: firstly, arranging a plurality of different independent heating temperature control loops at the position of a spacecraft, which needs to be heated and controlled; setting different thermal control modes according to different working condition requirements of the spacecraft; and step three, in a temperature control period, circularly controlling the temperature of all enabled temperature control loops in the current thermal control mode by a plurality of time slices, and controlling the temperature of only a part of enabled temperature control loops in each time slice. By adopting the thermal control method, the power fluctuation of the heater in the spacecraft is small, the system power supply voltage is stabilized, and the risk of electronic equipment caused by the voltage fluctuation is reduced; the temperature control loop of the spacecraft can be independently controlled, parameters are set, and the spacecraft can adapt to flexible switching of different thermal control modes; the total power peak value of the heaters of all the temperature control loops of the spacecraft is controllable, and the requirement of thermal control heating power on the power supply peak value power is reduced.
Description
Technical Field
The invention relates to the technical field of spacecraft control, in particular to a spacecraft autonomous thermal control method based on power balance.
Background
To accommodate complex space environments, spacecraft typically include thermal control systems to ensure that the equipment operates within a reasonable temperature range. In addition to the measures of coating the equipment, embedding the heat pipe and the like, the method for heating the equipment by converting electric energy into heat energy by using a heater is a common active thermal control measure when the temperature of the equipment is low. The heater management control technology is one of the key factors influencing the thermal control effect of the spacecraft.
In the prior art, patent CN201711250499.1 relates to a spacecraft thermal control management system, which includes: the control units are configured in each area of the spacecraft according to the thermal control requirement of the spacecraft, and are used for realizing the thermal control of each area of the spacecraft; and the data management computer is connected with the control single machines through a bus and is used for realizing the control of the control single machines and the information interaction among the control single machines. The invention carries out global consideration on the thermal control design of the spacecraft, uniformly configures thermal control resources and improves the thermal control efficiency. CN201811492069.5 patent proposes a spacecraft comprising a temperature control system, which comprises: the device comprises at least one temperature sensor, a control unit and a control unit, wherein each temperature sensor of the at least one temperature sensor is arranged on a temperature measuring point of a measured device and measures temperature data of the temperature measuring point, and the measured device comprises a plurality of target temperature control points positioned at other positions; a heating system that generates an additional temperature field to the measured device in an energized state; a temperature control unit that, in an operating state of the measured apparatus: receiving the at least one temperature measurement point temperature data measured by the at least one temperature sensor; judging the temperatures of the target temperature control points at other positions based on a pre-stored temperature field model of the measured equipment in a preset working state; and controlling a heating system to heat the measured equipment, and regulating and controlling the temperature of the target temperature control point.
The above method mainly has the following problems:
the method can solve the problems of single heating loop autonomous control and spacecraft thermal control management equipment layout communication, but the design of thermal control time sequences of all heating loops of the spacecraft is lacked, and the influence of the spacecraft thermal control on the consumed power is not considered. In some spacecraft with more thermally controlled loops, it is possible that thermally controlled heating power spikes may place greater capacity demands on the power subsystem.
Disclosure of Invention
In order to solve the problems in the prior art, the invention provides a spacecraft autonomous thermal control method based on power balance, which comprises the following steps:
firstly, arranging a plurality of different independent heating temperature control loops at the position of a spacecraft, which needs to be heated and controlled;
setting different thermal control modes according to different working condition requirements of the spacecraft;
and step three, in a temperature control period, circularly controlling the temperature of all enabled temperature control loops in the current thermal control mode by a plurality of time slices, and controlling the temperature of only a part of enabled temperature control loops in each time slice.
Furthermore, the temperature control loop comprises a plurality of thermistors for measuring the temperature of the target, a heater for heating the target and a switch thereof; each temperature control loop can independently perform heating temperature control and can be forbidden to control the temperature or can control the temperature.
Further, the second step further includes setting the enabling prohibition and temperature control threshold parameters of all temperature control loops in each thermal control mode.
Further, the second step further includes: dividing a thermal control mode in which the total thermal control power exceeds the power supply peak power into different sub-modes; the total power of the heaters in the temperature control loops enabled in each sub-mode does not exceed the peak power, and the temperature control loops enabled in all the sub-modes cover the temperature control loops required to control the temperature in the thermal control mode.
Furthermore, the same temperature control loop can be enabled in different sub-modes.
Furthermore, each sub-mode in the thermal control mode is periodically switched, in different sub-modes, the enabling state of the temperature control loop and the switching state of the heater are different, and the temperature control threshold is the same.
Furthermore, each sub-mode only enables a part of temperature control loops which need to be controlled in the current thermal control mode.
Further, the temperature control in the third step includes:
(1) measuring a target temperature and comparing the target temperature with the temperature control threshold;
(2) when the target temperature is lower than the lower limit of the temperature control threshold value and reaches a specified number of times continuously, closing the heater switch to heat the target; and when the target temperature is higher than the upper limit of the temperature control threshold value and reaches a specified number of times continuously, the heater is switched off.
Further, the heater of the temperature control loop is in a disconnected state by default.
Compared with the prior art, the invention has the beneficial effects that:
1. by adopting the thermal control method, the power fluctuation of the heater in the spacecraft is small, the system power supply voltage is stabilized, and the risk of electronic equipment caused by the voltage fluctuation is reduced;
2. the temperature control loop of the spacecraft can be independently controlled, parameters are set, and the spacecraft can adapt to flexible switching of different thermal control modes;
3. the total power peak value of the heaters of all the temperature control loops of the spacecraft is controllable, and the requirement of thermal control heating power on the power supply peak value power is reduced.
Drawings
FIG. 1 is a flowchart illustrating a temperature control operation of a temperature control loop according to an embodiment of the present invention;
fig. 2 is a flow chart of switching of thermal control sub-modes according to an embodiment of the present invention;
FIG. 3 is a schematic diagram illustrating a setting of a thermal control sub-mode according to an embodiment of the present invention;
Detailed Description
In order to make the technical problems solved, technical solutions adopted and technical effects achieved by the present invention clearer, the technical solutions of the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
According to the spacecraft autonomous thermal control method based on power balance, different independent heating temperature control loops are arranged at the position of a spacecraft needing heating temperature control according to the characteristics of the region, the heating power and the heating time, and each temperature control loop can independently carry out autonomous heating temperature control and parameter setting; in a control period, the loop is divided into a plurality of time slices for circulating temperature control, and each time slice controls the temperature of a part of the temperature control loop. And according to the working conditions, different thermal control modes are adopted, and the parameters of the temperature control loop are set. When power is limited, periodic thermal sub-mode control is performed within the thermal mode. The control flow charts of all temperature control loops and the control work flow charts of the thermal control sub-modes are respectively shown in fig. 1 and fig. 2, and the setting schematic diagram of the thermal control sub-modes of the temperature control loops is shown in fig. 3. The specific implementation is as follows:
the main and standby thermistors, the heater with certain power and the switch thereof are arranged at the position of the spacecraft needing heating and temperature control to form an independent temperature control loop with 8 paths. Each temperature control loop can independently control the temperature, the temperature control threshold value can be set, and the temperature control can be forbidden or enabled. And the heater is switched off when the temperature of the temperature control loop is continuously higher than the upper limit for 30s each time, and the temperature threshold value is collected for multiple times before the heater switch is controlled each time so as to prevent the influence of the field value which possibly appears. The total power of the thermal control of the spacecraft is controlled within 40W. The heater power conditions for each temperature control loop are shown in the following table:
| loop circuit | Power (W) |
| Loop 1 | 15 |
| Loop 2 | 10 |
| Loop 3 | 15 |
| Loop 4 | 15 |
| Loop 5 | 10 |
| Loop 6 | 15 |
| Loop 7 | 10 |
| Loop 8 | 10 |
Under a certain working condition, 1, 2, 3, 5 and 7 paths in 8 temperature control loops of the spacecraft need to be controlled, and the working condition is called as a thermal control mode 1. According to the thermal control analysis, only the power-on time of the heater of the temperature control loop 2 can exceed 50%, and other temperature control loops cannot exceed 50%. The thermal control mode 1 is divided into 2 sub-modes, the sub-mode 1 comprises temperature control loops 1, 2 and 5, the total power of the heaters is 35W, the sub-mode 2 comprises temperature control loops 2, 3 and 7, and the total heating power of the temperature control loops is 35W. The 2 sub-modes are periodically switched cyclically, each time for 2 minutes. When the sub-mode is switched, the enabling state of the temperature control loop needs to be set to be the state of the sub-mode, and the heater of the temperature control loop in the forbidden state needs to be disconnected.
According to the requirement of thermal control response time, a thermal control cycle is designed for 8s, time-sharing control is carried out in 8 time slices, and 1 temperature control loop is controlled for each time by 1s for each time slice. If the automatic temperature control of the temperature control loop is forbidden, no treatment is needed. If the acquired master thermistor of the temperature control loop exceeds a reasonable range, the thermistor is considered to be invalid, and a backup thermistor is used instead. Collecting the temperature of the thermistor exceeding the temperature control threshold range, updating the count of the exceeding threshold, and sending a heater closing or opening instruction by combining the current switch state when the temperature of the thermistor exceeds the temperature control threshold in 3 continuous control periods.
Although the invention has been described in detail hereinabove by way of general description, specific embodiments and experiments, it will be apparent to those skilled in the art that many modifications and improvements can be made thereto based on the invention. Accordingly, such modifications and improvements are intended to be within the scope of the invention as claimed.
Claims (9)
1. A spacecraft autonomous thermal control method based on power balance is characterized by comprising the following steps:
firstly, arranging a plurality of different independent heating temperature control loops at the position of a spacecraft, which needs to be heated and controlled;
setting different thermal control modes according to different working condition requirements of the spacecraft;
and step three, in a temperature control period, circularly controlling the temperature of all enabled temperature control loops in the current thermal control mode by a plurality of time slices, and controlling the temperature of only a part of enabled temperature control loops in each time slice.
2. The method of claim 1, wherein the temperature control loop comprises a plurality of thermistors for measuring the temperature of the target, a heater for heating the target, and switches thereof; each temperature control loop can independently perform heating temperature control and can be forbidden to control the temperature or can control the temperature.
3. The method according to claim 2, wherein the second step further comprises setting the disable enable and temperature control threshold parameters of all temperature control loops in each thermal control mode.
4. The method of claim 3, wherein the second step further comprises: dividing a thermal control mode in which the total thermal control power exceeds the power supply peak power into different sub-modes; the total power of the heaters in the temperature control loops enabled in each sub-mode does not exceed the peak power, and the temperature control loops enabled in all the sub-modes cover the temperature control loops required to control the temperature in the thermal control mode.
5. The method of claim 4, wherein the same temperature control loop can be enabled in different submodes.
6. The method of claim 4, wherein each sub-mode in the thermal control mode is periodically switched, and the enabling state of the temperature control loop and the switching state of the heater are different in different sub-modes, and the temperature control threshold is the same.
7. The method of claim 4, wherein each of said sub-modes enables only a portion of the temperature control loops that need to be controlled in the current thermal control mode.
8. The method of claim 4, wherein the controlling the temperature in step three comprises:
(1) measuring a target temperature and comparing the target temperature with the temperature control threshold;
(2) when the target temperature is lower than the lower limit of the temperature control threshold value and reaches a specified number of times continuously, closing the heater switch to heat the target; and when the target temperature is higher than the upper limit of the temperature control threshold value and reaches a specified number of times continuously, the heater is switched off.
9. The method according to any one of claims 2 to 8, wherein the heater of the temperature control circuit is in an off state by default.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113625803A (en) * | 2021-08-30 | 2021-11-09 | 上海卫星工程研究所 | Variable-power high-precision temperature control method, system, medium and equipment for spacecraft |
| CN114229043A (en) * | 2021-12-24 | 2022-03-25 | 中国电子科技集团公司第三十四研究所 | Intelligent active thermal control method of thermal control system based on power and temperature balance |
| CN114489180A (en) * | 2022-01-25 | 2022-05-13 | 北京卫星环境工程研究所 | Multi-zone independent temperature control method for thermal vacuum test |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113625803A (en) * | 2021-08-30 | 2021-11-09 | 上海卫星工程研究所 | Variable-power high-precision temperature control method, system, medium and equipment for spacecraft |
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| CN114489180A (en) * | 2022-01-25 | 2022-05-13 | 北京卫星环境工程研究所 | Multi-zone independent temperature control method for thermal vacuum test |
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