CN103036288B - Lithium ion storage battery additional charge controlling system - Google Patents
Lithium ion storage battery additional charge controlling system Download PDFInfo
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- CN103036288B CN103036288B CN201210526611.0A CN201210526611A CN103036288B CN 103036288 B CN103036288 B CN 103036288B CN 201210526611 A CN201210526611 A CN 201210526611A CN 103036288 B CN103036288 B CN 103036288B
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Abstract
The invention discloses a lithium ion storage battery additional charge controlling system which comprises a branch device, a charging device and a discharging device. The branch system is connected with an outer power supply bus through a circuit. The charging device is connected with a positive pole of an outer storage battery group through the circuit. The discharging device is connected with the positive pole of the outer storage battery group and the power supply bus through the circuit. The lithium ion storage battery additional charge controlling system is simple and practicable. Reliability of the satellite power supply system is improved.
Description
Technical field
The present invention relates to space power control technology field, particularly a kind of lithium-ions battery boost charge control system be applied in satellite failure situation.
Background technology
Spacecraft power supply system is spacecraft aerospace craft producing, stores, convert, regulate and distribute electric energy.Its basic function is by certain physical change or chemical change, and luminous energy, nuclear energy or chemical energy are converted to electric energy, carries out as required storing, regulate and converting, and then powers to each subsystem of spacecraft or equipment.Power-supply system is one of subsystem that spacecraft holds the balance, and its effect cans be compared to human heart, and the electric energy sent cans be compared to the blood of human body.
The solar photovoltaic power-supply system that overwhelming majority long-life spacecraft adopts is made up of solar battery array, lithium-ions battery group and power control unit.In illumination period, solar battery array, except the whole energy provided needed for spaceborne device, also needs to charge to lithium-ions battery group.In the ground shadow phase, solar battery array is not powered, and provides whole energy needed for spaceborne device by lithium-ions battery group.Take off at launching site, carrier rocket, enter the orbit before solar wing spreading, also powered by lithium-ions battery group.
Conventional satellite in GNC system (navigational guidance and the control system) situation that breaks down, without corresponding energy conservation measure.The satellite GNC system failure will cause Satellite vapour image can not Direct to the sun, make solar battery array power output, electric current degradation.The whole satellite load power losing solar battery array energy will be provided by storage battery, and this will cause the degree of depth overdischarge of lithium-ions battery group, and serious meeting causes the eventual failure of lithium-ions battery group.Lithium-ions battery group is as accumulation power supply unique on star, and its eventual failure causes the whole Star to give up the most at last.The present invention proposes a kind of lithium-ions battery boost charge control system be applied in satellite failure situation, promptly discharge switch is disconnected under satellite breaks down situation, prevent the overdischarge of lithium-ions battery group, having under illumination condition for lithium-ions battery group is charged, to wait for that ground control system is repaired GNC system simultaneously.For reducing loss, redemption satellite provides chance.This control system simple possible, improves the reliability of satellite power system.At present both at home and abroad without correlative theses or patent documentation.
Summary of the invention
The object of this invention is to provide a kind of lithium-ions battery boost charge control system, this control system simple possible, improves the reliability of satellite power system.
In order to realize above object, the present invention is achieved by the following technical solutions:
A kind of lithium-ions battery boost charge control system, comprises:
Part flow arrangement, described separate system is connected with the power supply buses of outside by circuit;
Charging device, described charging device is connected by the positive pole of circuit with the batteries of outside;
Electric discharge device, described electric discharge device is connected with the positive pole of the batteries of outside and power supply buses respectively by circuit.
Described part flow arrangement comprises connects successively: shunting solar battery array, shunt circuit, shunt diode; The described output of shunting solar battery array is connected with the input of shunt circuit, and this shunting solar battery array provides shunt circuit power; The output of described shunt circuit connects the anode of shunt diode; The negative terminal of described shunt diode connects outside power supply buses.
Described charging device comprises connects successively: charging solar battery array, charging circuit, charging diode and backward diode; The described output of charging solar battery array is connected with the input of charging circuit, and this charging solar battery array provides charging circuit power; The output of described charging circuit is connected with the anode of charging diode; The negative terminal of described charging diode is connected with the anode of backward diode; The negative terminal of described backward diode is connected with the positive pole of the batteries of outside.
Described electric discharge device comprises connects successively: discharge switch, discharge circuit and discharge diode; Described discharge switch and backward diode are connected in parallel, and its input is connected with the positive pole of the batteries of outside and the negative terminal of backward diode, and its output is connected with the input of discharge circuit and the anode of backward diode; The output of described discharge circuit is connected with the anode of discharge diode, and the negative terminal of described discharge diode is connected with the power supply buses of outside.
Also comprise: battery tension sample circuit, the sampling end of described battery tension sample circuit is connected by the positive pole of circuit with the batteries of outside, and its output externally sends sampled signal.
The present invention compared with prior art, has the following advantages:
1, under satellite breaks down situation, promptly disconnect discharge switch, protection lithium-ions battery group, be the charging of lithium-ions battery group having under illumination condition, for reducing loss, redemption satellite provides chance simultaneously.
2, the boost charge realized under lithium-ions battery failure condition by analog circuit is controlled, and circuit structure is simple and easy to realize and reliability is high, has important engineer applied and is worth.
Accompanying drawing explanation
Fig. 1 is the circuit theory diagrams of a kind of lithium-ions battery boost charge of the present invention control system.
Embodiment
Below in conjunction with accompanying drawing, by describing a preferably specific embodiment in detail, the present invention is further elaborated.
As shown in Figure 1, a kind of lithium-ions battery boost charge control system, comprises: part flow arrangement, charging device, electric discharge device.Wherein, separate system is connected with the power supply buses 9 of outside by circuit; Charging device is connected by the positive pole of circuit with the batteries 8 of outside; Electric discharge device is connected with the positive pole of the batteries 8 of outside and power supply buses 9 respectively by circuit.In the present invention, power supply buses 9 is for providing the power supply buses of work energy for satellite.
As shown in Figure 1, part flow arrangement comprises and connects successively: shunting solar battery array 1, shunt circuit 3, shunt diode D1; Wherein, the output of shunting solar battery array 1 is connected with the input of shunt circuit 3, this shunting solar battery array 1 provides shunt circuit 3 power, the output of shunt circuit 3 connects the anode of shunt diode D1, the negative terminal of shunt diode D1 connects outside power supply buses 9, by shunt circuit 3, the power that shunting solar battery array 1 inputs is carried out shunt regulating according to the technical requirement of satellite load, to ensure power supply buses 9 voltage stabilization.
As shown in Figure 1, charging device comprises and connects successively: charging solar battery array 2, charging circuit 4, charging diode D2 and backward diode D4; Wherein, the output of charging solar battery array 2 is connected with the input of charging circuit 4, this charging solar battery array 2 provides charging circuit 4 power, and the output of charging circuit 4 is connected with the anode of charging diode D2, and the negative terminal of charging diode D2 is connected with the anode of backward diode D4; The negative terminal of backward diode D4 is connected with the positive pole of batteries 8.
As shown in Figure 1, electric discharge device comprises and connects successively: discharge switch 6, discharge circuit 5 and discharge diode D3; Discharge switch 6 and backward diode D4 are connected in parallel, and its input is connected with the positive pole of batteries 8 and the negative terminal of backward diode D4, and its output is connected with the input of discharge circuit 5 and the anode of backward diode D4; The output of described discharge circuit 5 is connected with the anode of discharge diode D3, and the negative terminal of discharge diode D3 is connected with power supply buses 9.In the present embodiment, in normal operating conditions, discharge switch 6 is in closure state, and in satellite failure situation, discharge switch 6 is in off-state; Therefore, under discharge switch 6 closes situation, batteries 8 energy inputs discharge circuit 5 after discharge switch 6, and discharge circuit 5 carries out electric discharge according to the technical requirement of satellite load to batteries 8 energy and regulates, and inputs power supply buses 9.
As shown in Figure 1, because discharge switch 6 and backward diode D4 are connected in parallel, therefore, under discharge switch 6 closes situation, the power that charging solar battery array 2 inputs by charging circuit 4 carries out charging according to a customized type and regulates, and charging circuit 4 charges for batteries 8 through discharge switch 6; And under discharge switch 6 disconnection, it is batteries 8 boost charge that charging solar battery array 2, charging circuit 6 and diode D4 form loop.
In the present embodiment, also comprise: battery tension sample circuit 7, its sampling end is connected by the positive pole of circuit with the batteries 8 of outside, its output externally sends sampled signal, in the present embodiment, the voltage signal sampled is sent to Aerospace Control system by battery tension sample circuit 7.Namely in batteries 8 boost charge process, battery tension sample circuit 7 pairs of batteries 8 voltages are sampled and are fed back to outside Aerospace Control system, when batteries 8 voltage reaches the minimum voltage of batteries 8 permission, send discharge switch by Aerospace Control system to discharge switch 6 and lead to instruction, closed discharge switch 6, satellite recovers normal operating conditions.
In the present embodiment, shunt circuit 3, charging circuit 4, discharge circuit 5, battery tension sample circuit 7 all adopt prior art, wherein shunt circuit 3 adopts PWM-type shunting power regulating circuit, charging circuit 4 adopts PWM-type charge power regulating circuit, discharge circuit 5 adopts staggered-parallel-type step-up discharge circuit, and battery tension sample circuit 7 adopts electric resistance partial pressure type voltage sample circuit.
When deployed, the lithium-ions battery boost charge control system be applied in satellite failure situation has following two kinds of operating states:
1, satellite normal operation
Under satellite normal operation, described discharge switch 6 is in closure state, when the solar energy sailboard of satellite is in illumination period, the energy of shunting solar battery array 1 is supplied to power supply buses 9 after shunt circuit 3 regulates, meanwhile, the energy of charging solar battery array 2 charges for batteries 8 after overcharge circuit 4 regulates; When the solar energy sailboard of satellite is in the shade phase, batteries 8 energy is supplied to power supply buses 9 after discharge circuit 5 regulates.
2, satellite failure situation
Break down at satellite, need urgent when disconnecting discharge switch 6, batteries 8 no longer by discharge circuit 5 for power supply buses 9 provides energy.Due to backward diode D4 in parallel on discharge switch 6, can utilize the characteristic of diode unilateral conduction, charging solar battery array 2, charging circuit 4, backward diode D4 and batteries 8 form loop, charge having under light conditions for batteries 8.Battery tension sample circuit 7 pairs of batteries 8 voltages are sampled and feed back to Aerospace Control system, when batteries 8 voltage reaches the minimum voltage of batteries 8 permission, send discharge switch by Aerospace Control system to discharge switch 6 and lead to instruction, closed discharge switch 6, satellite recovers normal operating conditions, reaches the object retrieving whole star.
In sum, a kind of lithium-ions battery boost charge of the present invention control system, simple possible, improves the reliability of satellite power system.
Although content of the present invention has done detailed introduction by above preferred embodiment, will be appreciated that above-mentioned description should not be considered to limitation of the present invention.After those skilled in the art have read foregoing, for multiple amendment of the present invention and substitute will be all apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (1)
1. a lithium-ions battery boost charge control system, is characterized in that, comprises:
Part flow arrangement, described separate system is connected with outside power supply buses (9) by circuit;
Described part flow arrangement comprises connects successively: shunting solar battery array (1), shunt circuit (3), shunt diode (D1); The output of described shunting solar battery array (1) is connected with the input of shunt circuit (3), and this shunting solar battery array (1) provides shunt circuit (3) power; The output of described shunt circuit (3) connects the anode of shunt diode (D1); The negative terminal of described shunt diode (D1) connects outside power supply buses (9);
Charging device, described charging device is connected by the positive pole of circuit with outside batteries (8);
Described charging device comprises connects successively: charging solar battery array (2), charging circuit (4), charging diode (D2) and backward diode (D4); The output of described charging solar battery array (2) is connected with the input of charging circuit (4), and this charging solar battery array (2) provides charging circuit (4) power; The output of described charging circuit (4) is connected with the anode of charging diode (D2); The negative terminal of described charging diode (D2) is connected with the anode of backward diode (D4); The negative terminal of described backward diode (D4) is connected with the positive pole of outside batteries (8);
Electric discharge device, described electric discharge device is connected with the positive pole of the batteries (8) of outside and power supply buses (9) respectively by circuit;
Described electric discharge device comprises connects successively: discharge switch (6), discharge circuit (5) and discharge diode (D3); Described discharge switch (6) and backward diode (D4) are connected in parallel, its input is connected with the outside positive pole of batteries (8) and the negative terminal of backward diode (D4), and its output is connected with the input of discharge circuit (5) and the anode of backward diode (D4); The output of described discharge circuit (5) is connected with the anode of discharge diode (D3), and the negative terminal of described discharge diode (D3) is connected with outside power supply buses (9);
Also comprise: battery tension sample circuit (7), the sampling end of described battery tension sample circuit (7) is connected by the positive pole of circuit with outside batteries (8), and its output externally sends sampled signal.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210526611.0A CN103036288B (en) | 2012-12-10 | 2012-12-10 | Lithium ion storage battery additional charge controlling system |
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| CN201210526611.0A CN103036288B (en) | 2012-12-10 | 2012-12-10 | Lithium ion storage battery additional charge controlling system |
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| CN103036288A CN103036288A (en) | 2013-04-10 |
| CN103036288B true CN103036288B (en) | 2015-03-11 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103326445B (en) * | 2013-07-11 | 2016-05-18 | 上海空间电源研究所 | Bus is the lithium battery control system of regulative mode not |
| CN104393754B (en) * | 2014-10-21 | 2017-02-15 | 上海空间电源研究所 | Shunting control circuit of spacecraft power supply system and method thereof |
| CN105429182A (en) * | 2015-12-30 | 2016-03-23 | 哈尔滨工业大学 | Power source MPPT control system for satellite |
| CN105743206A (en) * | 2016-04-27 | 2016-07-06 | 中国人民解放军国防科学技术大学 | Four-level voltage trigger mechanism based satellite-borne power supply system |
| CN110148995B (en) * | 2019-04-17 | 2022-12-16 | 上海空间电源研究所 | Reconfigurable power supply system architecture of spacecraft |
| CN113507147A (en) * | 2021-06-15 | 2021-10-15 | 中国空间技术研究院 | PCU-NG and pre-charging method for connecting PCU-NG with lithium ion storage battery pack |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JP2001231184A (en) * | 2000-02-18 | 2001-08-24 | Nec Infrontia Corp | Backup circuit for portable apparatus |
| CN100365911C (en) * | 2006-03-02 | 2008-01-30 | 航天东方红卫星有限公司 | Accumulator charging controlling method |
| CN202997003U (en) * | 2009-12-04 | 2013-06-12 | 三洋电机株式会社 | Electric accumulation unit, power generating system and charge and discharge system |
| CN102324583B (en) * | 2011-09-01 | 2014-01-15 | 航天东方红卫星有限公司 | Lithium ion storage battery charging method based on sequential shunt switching regulation (S3R) |
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