RU2535301C2 - Method to control autonomous system of spacecraft power supply - Google Patents

Abstract

FIELD: electricity.

SUBSTANCE: invention is related to electric engineering and namely to power supply systems (PSS) of spacecraft using solar batteries as the primary energy sources and accumulator batteries as energy accumulators. The invention suggests a method for control of an autonomous system of a spacecraft power supply that contains a solar battery and n of the accumulator batteries, a voltage stabiliser coupled between the solar battery and the load and n of charge and discharge devices; the method lies in control of the voltage stabiliser and charge and discharge devices depending on the input and output voltage of the system, control of the charge and discharge degree of the accumulator batteries, prohibition of operation for the respective charge device when it reaches the charge limit of the accumulator battery, prohibition lifting when a certain discharge degree is reached by this accumulator battery, prohibition of operation for the respective discharge device when it reaches the discharge limit of the accumulator battery, prohibition lifting when a certain charge degree is reached by this accumulator battery, at that in case when the solar batteries lose their orientation to the Sun, in case of an emergency discharge of the accumulator batteries and switching-off of a part of the discharge devices when power of all the remaining discharge devices is insufficient for the load supply, operation of all devices is banned and after the recovery of the solar batteries orientation to the Sun control of the discharge devices is stopped against signals of the discharge level.

EFFECT: improved reliability of the system recovery process after emergency situations related to an unplanned deep discharge.

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Description

The invention relates to electrical engineering, namely, power supply systems (SES) of spacecraft (SC), using solar batteries (SB) as primary energy sources, and storage batteries (AB) as energy storage devices.

A known method of controlling an autonomous power supply system (RF patent No. 2059988, H02J 7/35) containing a solar battery (SB), a voltage regulator included between the solar battery and the load, "n" batteries (n ≥ 1) and "n" (according to the number of batteries) of charging and discharging devices, as well as for each battery - devices for controlling the degree of charge.

In the known SES, the voltage stabilizer, charging and discharge devices are continuously controlled depending on the input (voltage of the SB) and the output voltage of the SES. At the same time, the chargers provide a charge for the battery, and the voltage stabilizer and discharge device provide power to consumers.

The continuous control (feedback) circuits of the charger are connected to the SB bus and the load bus, and the continuous control circuits of the voltage stabilizer and discharge device are connected to the load bus.

Depending on the degree of charge or discharge of the battery, a ban or permit the operation of the charger and the discharge device is carried out.

Such management provides long-term autonomous operation of the SES. However, it does not ensure the preservation of the performance of SES in case of emergency or emergency situations on the spacecraft. In the event of an abnormal, unplanned violation of the orientation of the solar cells of the spacecraft to the sun, a violation of the energy balance in the SES occurs. If the loss of orientation is long enough, a complete discharge of all batteries may occur. Food on-board consumers will then stop.

A known method of controlling an autonomous power supply system (RF patent No. 2168828, H01J7 / 36) containing a solar battery and n rechargeable batteries, where n ≥ 1, is a voltage regulator connected between the solar panels and the load and over n charge and discharge devices, which consists in controlling voltage stabilizer and charge-discharge devices depending on the input and output voltage of the system, control of the degree of charge and discharged batteries, prohibition of the operation of the corresponding charger Upon reaching the maximum charge level of a given battery, removing this prohibition upon reaching a certain level of discharging a given battery, prohibiting the operation of a corresponding discharge device when reaching a maximum level of discharging a given battery, lifting this prohibition upon reaching a certain charge level of a given battery, characterized in that in the event of a loss of orientation of the solar panels in the sun, an emergency discharge of battery packs and disconnecting some of the discharge devices, when the power of the remaining discharge devices is not enough to power the load, the operation of all discharge devices is prohibited, and the discharge devices are no longer controlled by signals about the level of charge, after restoring the orientation of the solar batteries to the Sun, the batteries are first charged to a certain value of the capacitance, and then enable the operation of the discharge devices and resume control of the discharge devices by signals about the level of charge and.

This method is adopted as a prototype of the claimed invention.

The known method solves the problem of preventing the failure of batteries AB, restore the normal functioning of the SES after an emergency or emergency.

However, the known method does not give recommendations on the required value of the capacity of the batteries to ensure subsequent stable operation of the SES in this situation. When the battery is charged “up to a certain value of the capacity”, the value of this capacity may not be sufficient for operation in the standard configuration of the SES (permitting the operation of the discharge devices of the voltage stabilizer and the resumption of control of the discharge devices by signals about the level of charge), since then it takes a certain time to restore the standard orientation of the spacecraft (including the sun, which, incidentally, is done first of all). This can lead to a repeated blocking of the operation of the discharge devices and a failure of the output voltage of the SES, which will aggravate the already high degree of its emergency state.

The task of the invention is to increase the reliability of the process of restoring the SES after the emergencies associated with an unplanned deep discharge of batteries (loss of orientation of the spacecraft to the Sun).

The problem is solved in that when controlling an autonomous power supply system of a spacecraft containing a solar battery and n rechargeable batteries, a voltage stabilizer connected between the solar cells and the load and n charge and discharge devices, which consists in controlling the voltage stabilizer and charge-discharge devices in depending on the input and output voltage of the system, monitoring the degree of charge and discharged batteries, prohibiting the operation of the corresponding charge when reaching the maximum charge level of a given battery, removing this prohibition when a certain level of discharge of a given battery is reached, prohibiting the operation of a corresponding discharge device when reaching a maximum level of discharge of a given battery, lifting this ban when a certain level of charge of a given battery is reached, and in case of a loss of orientation of the solar panels in the sun, emergency discharge of batteries and disconnecting some of the discharge devices, when the capacity of the remaining discharge devices is not enough to power the load, prohibit the operation of all discharge devices and stop controlling the discharge devices by signals about the level of charge, after restoring the orientation of the solar batteries to the Sun, first charge the batteries to a certain value of capacity and then enable the operation of the discharge devices and resume control of the discharge devices by signals about the level of charge, after the formation of the orientation of solar batteries to the Sun before the resolution of the operation of discharge devices and the resumption of control of discharge devices by signals about the level of charge, charge the batteries to the energy intensity calculated based on the ratio:

∑ E _{AB1 ÷ n} ≥Р _but · T _but / K _ru · K _bks , where

∑ E _{AB1 ÷ n} - total energy intensity n AB;

P _but is the power consumed on the spacecraft in the initial orientation mode on the Sun;

T _but - the duration of the transition from an arbitrary position of the spacecraft in outer space to the initial orientation mode on the Sun;

To _ru - coefficient taking into account power losses in discharge devices;

K _bks - coefficient taking into account power losses in the onboard cable network.

During operation of the spacecraft during the discharge of any battery to the lower set level, this battery is transferred to storage mode (the discharge of this battery is blocked).

After disconnecting the corresponding discharge device, the load is powered by the remaining switched on discharge devices from other batteries that have not yet reached the established limit level of discharge.

If, after the prohibition of the operation of several discharge devices, the remaining power of the batteries and their discharge devices is insufficient to provide power to the on-board consumers, the operation of all discharge devices is prohibited. A signal to switch the SES to storage mode may also be a decrease in the voltage on the output buses of the SES below a certain value (with a lack of power of the working discharge devices, the output voltage of the SES will begin to decrease).

In the event of a random appearance of SB illumination (restoration of the SB orientation to the Sun to some extent) and an increase in voltage at the SES input, the battery will start to charge. In this case, you can unlock the operation of bit devices. However, premature removal of the blocking of the operation of discharge devices can lead to their repeated blocking due to the uncertainty of the spacecraft's position in outer space.

As an example, figure 1, shows a variant of the functional diagram of an autonomous spacecraft power supply system for implementing the proposed method.

The autonomous power supply system of the spacecraft contains: a solar battery 1 connected to the load 2 through a voltage converter 3, rechargeable batteries 4 ₁ -4 _n connected through the charging converters 5 ₁ -5 _n to the solar battery 1, and through the discharge converters 6 ₁ -6 _n - to the input of the output filter of the voltage converter 3. In addition, the batteries 4 ₁ -4 _n contain bypass discharge circuits consisting of diodes connected in parallel to each battery in the discharge direction.

At the same time, load 2 in its composition contains an on-board computer, a telemetry system and a command-measuring radio line.

In parallel to the batteries 4 ₁ -4 _n , the control devices for the batteries 7 ₁ -7 _n are connected, connected to the input with the batteries 4 ₁ -4 _n to control the voltage, pressure and temperature of the batteries, and the output to the load 2. In addition, control devices batteries 7 ₁ -7 _n contain discharge resistances (not shown in the diagram) for preventive discharges of batteries 4 ₁ -4 _n .

Measuring shunts 8 ₁ -8 _{n are} installed in the battery charge-discharge circuit.

Charging converters 5 ₁ -5 _n consist of a control key 9, controlled by a control circuit 10, a voltage boost unit made on a transformer 5-5, transistors 5-1 and 5-2 and a rectifier on diodes 5-3 and 5-4.

Bit converters 6 ₁ -6 _n consist of a control key 11, controlled by a control circuit 12.

The voltage converter 3 consists of a control key 13 controlled by a control circuit 14, an input filter on a capacitor 3-1 and an output filter on a diode 3-2, a choke 3-3 and a capacitor 3-4.

Control circuits 10 charging converters 5 ₁ -5 _n , 12 bit converters 6 ₁ -6 _n , 14 voltage converters 3 are made in the form of pulse-width modulators, the input connected to the stabilized voltage buses. The control circuit 10 of the charging converters 5 ₁ -5 _{n are} additionally connected with the measuring shunts 8 ₁ -8n and load 2.

The device operates as follows. During operation, rechargeable batteries 4 ₁ -4 _n work mainly in storage mode and periodic recharges from the solar battery 1 through charging converters 5 ₁ -5 _n . This mode of operation allows you to keep them in constant readiness for emergencies (loss of spacecraft orientation to the Sun) or for the passage of regular shadow areas of the orbit.

Power supply load 2 is provided from the solar battery 1 through the voltage Converter 3.

When passing shadow portions of the orbit, or if the spacecraft’s orientation to the Sun is disturbed, load 2 is powered by rechargeable batteries 4 ₁ -4 _n through discharge converters 6 ₁ -6 _n .

Monitoring devices 7 ₁ -7 _n control the voltage, pressure and temperature of the battery batteries 4 ₁ -4 _n and transmit information about their condition to the load 2.

During the operation of the spacecraft, according to the results of the analysis of information about the state of the battery (mainly the voltage of the batteries and the battery as a whole), according to the hardware logic or according to the program built into the on-board computer, a ban on the operation of all discharge devices is formed.

This situation will occur in the event of a loss of orientation of the solar cells of the spacecraft on the Sun, an emergency discharge of the batteries and disconnection of some of the discharge devices when the power of the remaining discharge devices is insufficient to power the load. In this case, the operation of all bit devices is prohibited.

After the restoration (partial or full) of the orientation of the solar batteries to the Sun, after increasing the voltage at the input of the SES, the batteries charge. At the same time, according to telemetry data (according to the parameters: pressure in the batteries - for nickel-hydrogen batteries or battery voltage - for lithium-ion batteries) in the flight control center on Earth, the total energy consumption of the batteries is calculated. The ban on the operation of discharge devices is removed by radio command from the Earth or automatically after charging the battery to the value of the total energy intensity, calculated based on the ratio:

∑ E _{AB1 ÷ n} ≥Р _but · T _but / K _ru · K _bks , where

∑ E _{AB1 ÷ n} - total energy intensity n AB;

P _but is the power consumed on the spacecraft in the initial orientation mode on the Sun;

T _but - the duration of the transition from an arbitrary position of the spacecraft in outer space to the initial orientation mode on the Sun;

To _ru - coefficient taking into account power losses in discharge devices;

K _bks - coefficient taking into account power losses in the onboard cable network.

This ensures that the spacecraft’s SES has enough energy (energy intensity) to switch to the initial orientation mode on the Sun, at which the spacecraft’s positive energy balance is guaranteed for the subsequent transition to the normal orientation mode of the spacecraft.

Thus, the claimed method of controlling an autonomous power supply system of a spacecraft provides an increase in the reliability of the process of restoring the SES after the emergencies associated with an unplanned deep discharge of batteries (loss of orientation of the spacecraft to the Sun).

Claims (1)

A method for controlling an autonomous power supply system of a spacecraft containing a solar battery and n rechargeable batteries, a voltage stabilizer included between the solar batteries and the load and n charging and discharging devices each, comprising controlling a voltage stabilizer and charge-discharge devices depending on the input and output voltage system, monitoring the degree of charge and discharged batteries, the prohibition of the operation of the appropriate charger when reaching a specific charge level of a given battery, lifting this prohibition upon reaching a certain level of discharge of a given battery, prohibiting the operation of a corresponding discharge device when reaching a maximum level of discharging a given battery, lifting this prohibition upon reaching a certain charge level of a given battery, and in case of loss orientation of solar panels on the Sun, emergency discharge of batteries and disconnection of part of discharge devices when the power of the remaining discharge devices is not enough to power the load, prohibit the operation of all discharge devices and stop controlling the discharge devices according to the charge level signals, after restoring the orientation of the solar batteries to the Sun, first charge the batteries to a certain value of capacity, and then allow the operation of the discharge devices and resume control of the discharge devices by signals about the level of charge, characterized in that after recovery rientatsii solar cells on the sun before discharge devices work resolution and the resumption control bit signals on the level of charge of the devices carried charge batteries to power consumption values, calculated from the ratio:
∑ E _{AB1 ÷ n} ≥Р _but · T _but / K _ru · K _bks , where
∑ E _{AB1 ÷ n} - total energy intensity n AB;
P _but is the power consumed on the spacecraft in the initial orientation mode on the Sun;
T _but - the duration of the transition from an arbitrary position of the spacecraft in outer space to the initial orientation mode on the Sun;
To _ru - coefficient taking into account power losses in discharge devices;
K _bks - coefficient taking into account power losses in the onboard cable network.

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