CN112583071A - Power supply system for deep space exploration separation monitoring satellite - Google Patents

Power supply system for deep space exploration separation monitoring satellite Download PDF

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Publication number
CN112583071A
CN112583071A CN202011355205.3A CN202011355205A CN112583071A CN 112583071 A CN112583071 A CN 112583071A CN 202011355205 A CN202011355205 A CN 202011355205A CN 112583071 A CN112583071 A CN 112583071A
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battery
temperature coefficient
circuit
coefficient thermistor
power supply
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CN112583071B (en
Inventor
吴迪
孙少勇
任冰
毛晓楠
安双新
杜洋
陆建
陈芳
彭伟栋
朱琦
杨奕晟
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Shanghai Aerospace Control Technology Institute
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Shanghai Aerospace Control Technology Institute
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    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0029—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries with safety or protection devices or circuits
    • H02J7/00309—Overheat or overtemperature protection

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  • Engineering & Computer Science (AREA)
  • Power Engineering (AREA)
  • Secondary Cells (AREA)

Abstract

The invention relates to a deep space detection separation monitoring satellite power supply system, which comprises a battery assembly and a battery protection circuit, wherein the battery protection circuit comprises a positive temperature coefficient thermistor, a negative temperature coefficient thermistor, a first capacitor and a second capacitor; the first capacitor and the second capacitor are connected in series and then connected in parallel with the negative temperature coefficient thermistor to form a parallel circuit, the first end of the parallel circuit is grounded, and the second end of the parallel circuit is connected with the first end of the positive temperature coefficient thermistor; the second end of the positive temperature coefficient thermistor is connected with the monitoring satellite circuit; the positive pole of the battery pack is connected with the second end of the parallel circuit, and the negative pole of the battery pack is grounded. The invention can ensure the health of the battery component under the conditions of deep space, high vacuum degree and severe temperature change.

Description

Power supply system for deep space exploration separation monitoring satellite
Technical Field
The invention relates to the field of deep space exploration, in particular to a power supply system after separation of a separation monitoring satellite.
Background
The spark detection separation satellite can be used at different stages of the spark detector. The method can be used for engineering measurement of the Mars detector. In the initial stage of launching, the solar wing can be unfolded and the related load can be unfolded for observation. In the ground fire transfer section, the monitoring satellites are separated, and the state of the whole Mars detector can be measured in engineering. In the ring fire segment, engineering measurement can be carried out on the states of the lander and the surrounding device of the Mars probe. When the separation satellite is fixedly connected with the mars detector body, namely, under the condition that the separation satellite is not separated, the storage health management needs to be carried out on the battery assembly in the deep space orbit environment, so that reasonable power supply can still be carried out after the separation monitoring half-satellite is separated.
The deep space environment refers to the temperature range of-55-75 ℃, and in order to ensure that the separation satellite is continuously powered after being separated, the battery assembly of the power supply system needs to be healthily managed in the non-separation stage of the separation satellite.
Disclosure of Invention
In order to achieve the above object, the present invention provides a power supply system for a monitoring satellite for Mars detection, which specifically comprises a battery assembly and a battery protection circuit;
the battery protection circuit comprises a positive temperature coefficient thermistor, a negative temperature coefficient thermistor, a first capacitor and a second capacitor;
the first capacitor and the second capacitor are connected in series and then connected in parallel with the negative temperature coefficient thermistor to form a parallel circuit, the first end of the parallel circuit is grounded, and the second end of the parallel circuit is connected with the first end of the positive temperature coefficient thermistor;
the second end of the positive temperature coefficient thermistor is connected with the monitoring satellite circuit;
the positive pole of the battery pack is connected with the second end of the parallel circuit, and the negative pole of the battery pack is grounded.
The battery assembly includes Li-MnO2Soft package battery, aluminum shell and connector, and Li-MnO2The soft package battery is packaged in the aluminum shell and is supplied with power through the connector.
The Li-MnO2The soft package battery can keep the battery activity in the environment temperature range of-50 ℃ to 70 ℃.
The resistance value of the positive temperature coefficient thermistor is not lower than 5M omega at the temperature of 80 ℃, so that the circuit is ensured to realize large resistance open circuit under the condition of overhigh temperature, and the purposes of protecting the battery pack and monitoring the satellite circuit are achieved.
The negative temperature coefficient thermistor has the resistance value not higher than 1.5M omega at the temperature of 62 ℃, so that the self-discharge of the battery assembly can be smoothly carried out under the condition of overhigh temperature, and the battery assembly has the micro-discharge capacity.
According to the deep space environment condition, the protection circuit is arranged between the monitoring satellite circuit and the battery component, compared with the prior art, the invention has the advantages and beneficial effects that:
the battery pack protection circuit is designed to ensure the health of the battery pack under the conditions of deep space, high vacuum degree and severe temperature change, and ensure the good state of the battery pack when a task is executed.
Drawings
FIG. 1 is an overall circuit block diagram of the deep space exploration split surveillance satellite of the present invention;
fig. 2 is a circuit schematic of the present invention.
Detailed Description
The present invention provides a deep space exploration separation monitoring satellite power supply system, which is further described in detail with reference to the accompanying drawings and the detailed description.
As shown in fig. 1, the circuit block diagram of the deep space exploration separation monitoring satellite of the present invention includes a monitoring satellite circuit, a battery pack protection circuit is externally disposed at a power supply interface end of the monitoring satellite circuit and is respectively connected with the monitoring satellite circuit and a battery pack through a circuit, and the battery pack protection circuit is used for maintaining battery activity of the battery pack and protecting the monitoring satellite circuit and the battery pack.
As shown in fig. 2, the present invention provides a power supply system for a monitoring satellite for Mars detection, which specifically includes a battery assembly P1 and a battery protection circuit electrically connected to the battery assembly P1;
the battery protection circuit comprises a positive temperature coefficient thermistor (PTC thermistor) MF2, a negative temperature coefficient thermistor (NTC thermistor) MF1, a first capacitor C11 and a second capacitor C12; the first capacitor C11 and the second capacitor C12 are connected in series and then connected in parallel with the negative temperature coefficient thermistor MF1 to form a parallel circuit, the first end of the parallel circuit is grounded, and the second end of the parallel circuit is connected with the first end of the positive temperature coefficient thermistor MF 2;
the second end of the positive temperature coefficient thermistor MF2 is connected with a monitoring satellite circuit;
the positive pole of the battery pack P1 is connected with the second end of the parallel circuit, 12.5V voltage is output to the monitoring satellite circuit through a positive temperature coefficient thermistor MF2, and the negative pole of the battery pack P1 is grounded.
Wherein the battery assembly P1 comprises Li-MnO2(Li-manganese dioxide) soft package battery, aluminum shell and connector arranged on the aluminum shell, wherein the Li-MnO is2The laminate polymer battery is packaged in the aluminum shell and is supplied with power through the connector.
In the deep space exploration process, the separated monitoring satellites receive different illumination conditions along with the difference of the orbit and the posture of the whole spacecraft. This also results in separate monitoring satellites that can experience temperature variations from-55 c to 75 c, which can last for months or even years in high temperature environments. In the case of high temperature, the battery pack needs to be discharged to maintain its own state. According to the invention, the NTC thermistor MF1 is connected in parallel, the resistance value of the resistor is large when the temperature is low, the function of open circuit is achieved, the resistance value of the resistor is reduced along with the rise of the temperature, a loop is formed between the positive electrode and the negative electrode of the battery assembly, and the activity of the battery can be ensured through micro current.
During the execution process of the deep space detection task, a single event effect occurs due to the influence of cosmic rays. The separation satellite is used as an optical, mechanical and electrical integrated product and needs to have the capability of resisting single particle locking. If the condition of single particle locking occurs in the separation satellite device, the phenomenon of abnormal large current can occur. In the process of executing the deep space exploration task, the remote control signal transmission time is as long as dozens of minutes to dozens of minutes due to the remote distance, and ground intervention cannot be carried out. The occurrence of large current also means that heat consumption is increased, the satellite battery assembly protection circuit is separated from the series connection of the PTC thermistor MF2 according to the characteristic, the resistance value of the series connection of the PTC thermistor MF2 is increased along with the increase of temperature, and when the temperature reaches a certain degree, an open circuit is formed, so that the battery assembly is protected and the satellite circuit is monitored.
Preferably, the Li-MnO2The soft package battery can keep the battery activity in the environment temperature range of-50 ℃ to 70 ℃. According to Li-MnO2The discharge principle of the soft package battery is as follows: during the discharge process, lithium ions in the negative electrode migrate to manganese dioxide in the positive electrode through the electrolyte and the separator, and during the process, ion migration occurs to discharge. The temperature can affect the electrolyte to further affect the activity of the battery, the electrolyte is formed by mixing lithium salt and an organic solvent, the organic solvent can be solidified at low temperature and cannot form lithium ion migration, the organic solvent can be gasified at high temperature to affect the lithium ion migration, and Li-MnO2The electrolyte used by the soft package battery has certain conductivity capability at-50 ℃ although the working performance is affected by low temperature, so that the soft package battery can work; the solvent and additive used in the electrolyte make the electrolyte at 8Vaporization is possible above 0 ℃ and therefore the Li-MnO should be maintained below 80 DEG2The soft package battery works normally, so the temperature range of-50 ℃ to 70 ℃ is a proper working temperature range.
Selecting a thermistor meeting the requirement according to the temperature curve of the thermistor, wherein specifically, the resistance value of the selected positive temperature coefficient thermistor is not lower than 5 MOmega at the temperature of 80 ℃; the selected negative temperature coefficient thermistor has a resistance value not higher than 1.5 MOmega at a temperature of 62 ℃.
In this embodiment, the deep space environment is simulated through experiments, which are as follows:
under the laboratory state, the single-particle striking separation monitoring satellite is used, and the separation monitoring satellite is influenced by the single-particle effect and can generate a normal current state 1.5-2 times. Under the state, the temperature of the power supply bus of the whole separation monitoring satellite battery assembly rises to about 95 ℃, and the temperature change curve of the power supply bus of the battery assembly under the condition that high current appears under the normal working state is obtained.
The PTC thermistor MF2 is selected according to the temperature change curve. The resistance of the resistor needs to be matched with the temperature change curve as much as possible. Under normal temperature (25 ℃ +/-2 ℃) and normal pressure and normal working state, the separation monitoring satellite works normally, and the temperature of the self heating battery component rises to 32 ℃. In a deep space state, the temperature of the separation monitoring satellite can be kept within a range of-10 ℃ to 0 ℃ by thermal control measures, and the temperature of a power supply bus of the battery assembly can be increased to about 80 ℃ after a single event effect occurs in the deep space state. Namely, under the condition of 80 ℃, the resistance value of the PTC thermistor MF2 is selected to be not less than 5M omega.
After selection, the separation monitoring satellites are placed in a low-temperature box to be cooled to-30 ℃. And taking out the separation monitoring satellite to perform single-particle striking within 2 minutes, so that a single-particle effect occurs. And checking the correctness of the selected PTC thermistor. Tests show that the selected PTC thermistor needs to have resistance value rise at 77 ℃ to form open circuit, and the deep space application condition can be met.
The NTC thermistor MF1 is selected from the NTC thermistor MF1, and is used for ensuring the activity of the battery component under the high-temperature condition. Battery packAt high temperatures, Li-MnO2A self-discharge phenomenon occurs. Under the condition of long-term high temperature, the battery pack can not work normally when in use. To avoid this, the battery pack can be activated during the micro-discharge at high temperature.
In extreme cases, the separate satellites are mounted on the side of the Mars probe and illuminated, and the temperature rises to about 62 ℃ at maximum. In this case, Li-MnO2A self-discharge path is required to ensure the activity of the battery without damaging the battery. The resistance value of the NTC thermistor MF1 reaches 1.5M omega at 62 ℃, so that the battery assembly has micro-discharge capacity.
The invention sets a protection circuit between the monitoring satellite and the battery pack according to the deep space environment condition. Compared with the prior art, its advantage and beneficial effect are:
the battery pack protection circuit is designed to ensure the health of the battery pack under the conditions of deep space, high vacuum degree and severe temperature change, and ensure the good state of the battery pack when a task is executed.
While the present invention has been described in detail with reference to the preferred embodiments thereof, it should be understood that the above description should not be taken as limiting the invention. Various modifications and alterations to this invention will become apparent to those skilled in the art upon reading the foregoing description. Accordingly, the scope of the invention should be determined from the following claims.

Claims (5)

1. A power supply system for a deep space detection separation monitoring satellite is characterized by comprising a battery assembly and a battery protection circuit, wherein the battery protection circuit comprises a positive temperature coefficient thermistor, a negative temperature coefficient thermistor, a first capacitor and a second capacitor;
the first capacitor and the second capacitor are connected in series and then connected in parallel with the negative temperature coefficient thermistor to form a parallel circuit, the first end of the parallel circuit is grounded, and the second end of the parallel circuit is connected with the first end of the positive temperature coefficient thermistor;
the second end of the positive temperature coefficient thermistor is connected with the monitoring satellite circuit;
the positive pole of the battery pack is connected with the second end of the parallel circuit, and the negative pole of the battery pack is grounded.
2. The power supply system of claim 1 wherein said battery assembly comprises Li-MnO2Soft package battery, aluminum shell and connector, and Li-MnO2The soft package battery is packaged in the aluminum shell and is supplied with power through the connector.
3. The power supply system of claim 2 wherein said Li-MnO2The soft package battery can keep the battery activity in the environment temperature range of-50 ℃ to 70 ℃.
4. The power supply system of claim 1 wherein the ptc thermistor has a resistance of no less than 5M Ω at a temperature of 80 ℃.
5. The power supply system of claim 1 wherein said ntc thermistor has a resistance of no more than 1.5M Ω at a temperature of 62 ℃.
CN202011355205.3A 2020-11-27 2020-11-27 Power supply system for deep space exploration separation monitoring satellite Active CN112583071B (en)

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Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1101986A (en) * 1976-07-14 1981-05-26 Frans Slegers Degaussing circuit in a colour television receiver
CN101884126A (en) * 2008-11-10 2010-11-10 大井Em株式会社 Cathode active material for lithium secondary batteries with high safety and method of preparing for the same and lithium secondary batteries comprising the same
CN103384071A (en) * 2012-05-02 2013-11-06 纬创资通股份有限公司 Battery charging circuit
CN103594758A (en) * 2013-10-31 2014-02-19 航天东方红卫星有限公司 Satellite-borne storage battery dual-interval autonomous temperature control method
CN108075761A (en) * 2017-12-26 2018-05-25 积成电子股份有限公司 A kind of on-off model processing method of temperature self-compensation
CN211178757U (en) * 2019-12-31 2020-08-04 广东电网有限责任公司 Temperature measuring device
CN111930171A (en) * 2020-09-27 2020-11-13 中国兵器工业集团第二一四研究所苏州研发中心 Low-temperature-drift precision voltage output circuit

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CA1101986A (en) * 1976-07-14 1981-05-26 Frans Slegers Degaussing circuit in a colour television receiver
CN101884126A (en) * 2008-11-10 2010-11-10 大井Em株式会社 Cathode active material for lithium secondary batteries with high safety and method of preparing for the same and lithium secondary batteries comprising the same
CN103384071A (en) * 2012-05-02 2013-11-06 纬创资通股份有限公司 Battery charging circuit
CN103594758A (en) * 2013-10-31 2014-02-19 航天东方红卫星有限公司 Satellite-borne storage battery dual-interval autonomous temperature control method
CN108075761A (en) * 2017-12-26 2018-05-25 积成电子股份有限公司 A kind of on-off model processing method of temperature self-compensation
CN211178757U (en) * 2019-12-31 2020-08-04 广东电网有限责任公司 Temperature measuring device
CN111930171A (en) * 2020-09-27 2020-11-13 中国兵器工业集团第二一四研究所苏州研发中心 Low-temperature-drift precision voltage output circuit

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