RU2322373C2 - Method of control of spacecraft solar battery position and system for realization of this method - Google Patents

Abstract

FIELD: spacecraft systems for supply of power with the aid of solar batteries.

SUBSTANCE: proposed method includes turning of solar batteries to the working position corresponding to matching of normal to their illuminated surface with plane formed by axis of rotation of solar battery panels and direction to the Sun. Proposed method includes also measurement of density of fluxes of solar electromagnetic radiation and high-energy particles determining the moments of beginning of solar activity and arrival of said particles to spacecraft surface. Additional measurement includes determination of appearance of signs of negative action of particle flux on spacecraft. During these moments, onboard solar batteries are charged to maximum level. When density of particle flux exceeds threshold magnitude, solar battery panels are turned through angle between said normal and direction to the Sun corresponding to minimum action of particle fluxes on solar battery surfaces. Discharge of storage batteries is hoped to close the energy gap on board the spacecraft. At minimum permissible level of storage battery charge, storage batteries are disconnected from load. When action of particles on spacecraft is discontinued, solar battery panels are returned to working position. System proposed for realization of this method includes units and their couplings for performing the above-mentioned operations. System is provided with unit for determination of current from solar batteries, unit for determination of moments of appearance of signs of negative action of high-energy particles on spacecraft and unit for setting the permissible level of charge of storage batteries.

EFFECT: reduction of negative action of high-energy particle flux on solar battery working surface due to maximum increase of angle of "protective" turn of solar batteries from direction of these fluxes to the Sun.

3 cl, 1 dwg

Description

The invention relates to the field of space technology, in particular to power supply systems (SES) of spacecraft (SC), and can be used to control the position of their solar panels (SB).

A known method of controlling the position of the panels SB, adopted as an analogue (see [1], pp. 190-194). The essence of the method is as follows. SB panels are oriented in such a way that the angle between the normal to their illuminated work surface and the direction to the Sun is the minimum value, which ensures the maximum energy input from the SB.

To ensure high efficiency of the SB, most spacecraft install a system for their automatic orientation to the sun. The composition of such a system includes solar sensors, logically converting devices and electric drives that control the position of the SB.

The disadvantage of this method and control system for the position of the SC SB is that their actions do not provide protection against the negative impact of environmental factors (PF) on the working surfaces of the SB panels, such as protection against gases coming out of working jet engines (RD) ) Spacecraft (see [2], pp. 311-312; [3], pp. 2-27), and fluxes of protons and high-energy electrons of cosmic rays of solar electromagnetic radiation (EMP) during periods of high solar activity (see [ 2], p. 323; [7], p. 31, 33).

The closest of the analogues adopted for the prototype is a method of controlling the position of the SC SC, described in [12]. The essence of the method is as follows.

They turn the SB panels into a working position, providing the spacecraft with electric power, corresponding to combining the normal to its illuminated working surface with the plane formed by the axis of rotation of the SB panels and the direction to the Sun. Next, determine the time point of the beginning of the negative impact of the PF on the working surface of the SB and turn the SB panels to the time of the beginning of the impact of these factors and return the SB panels to their working position after the end of the specified exposure. To do this, measure the density of the current flux of solar electromagnetic radiation and from the measured values determine the time moment of the onset of solar activity, determine the time when the particles reach the high energies of the spacecraft's surface. At a specified point in time, the flux density of high-energy particles — protons and electrons — is measured and the measured values are compared with threshold values. If the measured values of the threshold values of the proton and electron fluxes exceed, the SB panels are rotated by an angle between the normal to their illuminated working surface and the direction α _{s_min} to the Sun, corresponding to the minimum area of influence of high-energy particle fluxes on the SB surface, determined by the ratio:

α _{s min} = arccos (I _n / I _m ),

where I _n - load current from spacecraft consumers;

I _m is the maximum current generated when the illuminated working surface of the SB panels is oriented perpendicular to the sun's rays,

at the same time, the time of the beginning of the turn of the SB panels is taken to be the time when the measured values exceed the upper threshold flux density of these high-energy particles, and the time of the start of the return of the SB panels to the working position is taken to be the time at which the density of high-energy particle flows becomes lower threshold value.

SB in the ISS SES system are the main sources of electricity and ensure the operation of its onboard consumers, including recharging batteries (AB), which are secondary sources of electricity onboard the ISS (see [4]). By turning the SB decreases the area of damage to the working surfaces of the SB flow of the FVS. It is not possible to fully deploy the SB panels along the damaging flow of the FVC, because it is necessary to provide the spacecraft and its batteries with electricity generated by the SB, - based on this, the area of damage to the SB panels by the flow of high-energy particles is reduced to the minimum by turning the SB through an angle α _{s min} , which is necessary and sufficient to provide on-board consumers with energy.

Based on the necessary sufficiency, for the operation of the spacecraft onboard systems, the load from consumers I _n should not exceed the current current I. Since the current current I from the SB is determined by the expression (see [9], p. 109)

where I _m is the maximum current generated when the illuminated working surface of the solar panels is oriented perpendicular to the sun's rays;

α is the current angle between the normal to the working surface of the SB and the direction to the Sun,

then the current angle α should not exceed the value of α _{s min} calculated by the formula:

The SB position control system for implementing this method, adopted as a prototype, is described in [12] and contains a SB, on the rigid substrate of which four photovoltaic batteries are located (BF ₁ , BF ₂ , BF ₃ , BF ₄ ), a SB rotation device (UPSB ); amplifier-converting device (UPU); control unit for the orientation of the SB in the direction to the Sun (BSOSBS); SB turn block in a predetermined position (BRBSPZ); two current regulators (PT ₁ , PT ₂ ), block AB (BAB); charger for AB (ZRU AB); unit for forming teams for the charge of AB (BFKZ AB); load current sensor (DTN); power supply system control unit (BUSES); power supply bus (ШЭ); a unit for measuring the density of the current flow of solar EMP (BIPEMI); unit for determining solar activity (BOS); a unit for determining the time moment of the particle impact on the spacecraft (BOMVHF); unit for measuring the density of fluxes of particles of high energy (BIPPCHVE); a unit for determining the timing of the start of the SB control by load currents (BOMVUSBTNZ); SB control unit for load currents (BUSBTNZ). In this case, the SB through its first output, combining the outputs of BF ₁ and BF ₄ , is connected to the first input of UPSB, and through the second output, combining the outputs of BF ₂ and BF ₃ , is connected to the second input of UPSB. The outputs of the БУОСБС and БРСБЗП are connected respectively to the first and second inputs of the UPU, the output of which, in turn, is connected to the third input of the UPSB. The first and second outputs of the UPSB are connected respectively to the inputs of PT ₁ and PT ₂ , and the outputs of PT ₁ and PT _{2 are} connected to the ST. BAB with its entrance through the ZRU AB is connected to the SE. At the same time, the switchgear switchgear is connected by its first input to the specified bus, and the accident output is connected to the second switchgear switchgear input, the input of which is connected, in turn, to the ШЭ. BAB with its output is connected to the first input of the BFKZ AB, and the first output of the BUSES is connected to the second input of the indicated block. The output of the BFKZ AB is connected to the third input of the ZRU AB. The second and third outputs of the BUSES are connected respectively to the first inputs of the BUSSBS and BRBSP. The third output of the UPSB is connected to the second inputs of the BUOSBS and BRBSBZP. The BIPEMI output is connected to the BOS input, the first output of which, in turn, is connected to the BOMHF input. The outputs of the BOMVCH and BIPCHVE are connected to the first and second inputs of the BOMVUSBTNZ block, respectively, and the input of the BIPCHCH is connected to the second output of the BFBCH. The output of the BOMVUSBTNZ is connected to the input of the BUSES. The BUSES with its fourth output is connected to the first input of the BUSTNZ, and the second output of the DTN is connected to the second input of the BUSBTNZ. The output of the BUSBTNZ is connected to the third input of the UPU. In addition, the third output of the UPSB is connected to the third input of the BUSBTNZ.

In the power supply mode of the spacecraft, the system operates as follows.

UPSB serves for the transit of electricity from SB to PT ₁ and RT ₂ . Voltage stabilization on the power supply bus of the SES is carried out by one of the RTs. At the same time, another RT is in a state with closed power transistors. SB generators work in this case in a short circuit mode. When the load power becomes more than the power of connecting the SB generators, another RT switches to voltage stabilization mode, and the energy of the idle generators goes to the power supply of the SES. In certain periods, when the load power can exceed the power of the SB, ZRU AB, due to the discharge of the AB block, it compensates for the shortage of electricity on board the spacecraft. For these purposes, the AB discharge regulator serves as an AB discharge regulator.

In addition to the specified regulator ZRU AB also contains a charge regulator AB. The charge regulator restricts the BAB charge current at the level of (I _nc ± 1) A, where I _nc is the nominal charge current, with excess power of the BF and voltage stabilization on the SES bus by regulating the charge current of the BAB with the BF power insufficient to provide battery power charge current (I _nz ± 1) A. To carry out the indicated charge-discharge cycles in the indoor switchgear AB information from the DTN is used. In this case, the DTN is connected to the SES in such a way that it measures the load current not only from on-board consumers, but also takes into account the charge current of the battery. BAB charge is carried out by ZRU AB through BFKZ AB.

Simultaneously with the operation in the spacecraft power supply mode, the system solves the problem of controlling the position of the planes of SB panels.

On command from the BUSES, the BUOSBS unit controls the orientation of the SB to the Sun. BUOSBS can be implemented on the basis of the spacecraft navigation and navigation system (VESS) of the spacecraft (see [6]). In this case, the input information for the SB control algorithm is: the position of the unit direction vector on the Sun relative to the coordinate axes associated with the spacecraft, determined by the algorithms of the KIND kinematic contour; the position of the SB relative to the spacecraft body, obtained in the form of the current measured values of the angle α from the angle sensors (DU) installed on UPSB. In this case, the value of α is always measured from the current normal to the working surface of the SB (i.e., when the SB is oriented to the Sun, α is minimal). The output of the control algorithm are commands for rotating the SB relative to the axis of the output shaft of the UPSB and commands for stopping rotation. Remote control UPSB give discrete signals about the position of the SB. The value of the discrete determines the accuracy of the orientation of the SB.

In the normal mode of orientation of the spacecraft, when the direction of the sun’s movement relative to the connected axes of the spacecraft is unchanged, the SB is set relative to the direction of the sun ahead of the sun in the direction corresponding to several discrete remote control. Further, the battery remains in this position until the Sun, due to the motion of the spacecraft in orbit, "moves forward" relative to the SB by an appropriate angle. After that, the rotation cycle resumes.

BRBSZP controls SB with the help of BUSES according to program settings. The SB control algorithm according to the program settings allows you to install the battery in any given position. For this, an initial signal is issued to the BUOSBS about the installation of the SB in the initial position. Then, using the BUSBZP, the required turn through the angle α _{z is} carried out. At the same time, information from the remote control of the UPSB is also used to control the pivot angle in the BRBSP.

UPU plays the role of an interface between the BSECS, BRBSPZ, BUSBTNZ and UPSB.

BIPEMI continuously measures the current fluxes of solar electromagnetic radiation (EMP) from the solar activity index F10.7 and transmits them to BOS. In BOS, by comparing the current values with the given thresholds, the onset of the activity of the Sun is determined. According to the command coming from the first output of the biofeedback to the input of the BOMHF, the specified last block determines the time moment of the possible onset of the impact of high-energy particles on the spacecraft. From the second output of the BOSF through the BIPCHVE input, a command is issued to start measuring the flux density of high-energy particles. Information about the time instant of the possible onset of particle impact on the spacecraft is transmitted from the BOMVCH output to the BOMVUSBTNZ through its first input. At the second input of the BOMVUSBTNZ, the measured value of the density of fluxes of high-energy particles from BIPCHVE is transmitted.

In BOMVUSBTNZ, an actual assessment of the negative impact of the PFV is carried out by comparing the current measured value of the exposure characteristic with threshold values, starting from the point in time determined by the BOMVHF. A necessary condition for receiving a command at the output of the BOMVUSBTNZ is the presence of two signals - from the outputs of the BOMVVCH and BIPPCHVE. At the output of the BOMVUSBTNZ, the command “start control of the power supply by load currents” is formed, which enters the BUSES.

When the BOMVUSBTNZ issues a command to the BUSSES, the command received from the BOMVUSBTNZ is higher in priority than the teams for engaging the BSBUS and BRBSP. Therefore, having received the indicated command, the BUSEC disables lower priority blocks from the UPSB control and connects the BUSTS.

After resetting the team with BOMVUSBTNZ at the input of the BUSES, the latter rebuilds the logic of its work. Depending on the spacecraft flight program being carried out, priority for SB control is given to one of the BUOSBS or BRSBZP blocks.

BUSTNZ determines the angle α _{s_min} by the expression (2). To calculate the specified angle, the measured values of I _n obtained from DTN are used. In addition, with the remote control of the UPSB, the indicated unit receives information about the current value of the angle of rotation of the SB α. Having determined the value of the angle α _{s_min} , the algorithm embedded in the BUSBTNZ compares it with the current value of the angle α, calculates the angle of mismatch between α and α _{s_min} and the required number of control pulses to activate the SB control drive. Control pulses are transmitted to the UPA. After converting and amplifying the indicated pulses into the UPA, they arrive at the input of the UPSB and drive the drive.

The method and system for its implementation, adopted as a prototype, has a significant drawback - they do not provide complete protection of the SB surface from the negative effects of high-energy particle flows, and at the same time they do not allow additional opportunities to reduce this negative impact due to special operations for preparing SES SPACECRAFT to work under conditions of the negative impact of high-energy particle flows on SPACECRAFT

The challenge facing the proposed method and system for its implementation is to reduce the negative impact of high-energy particle flows on the surface of the SB. To this end, due to the implementation of special preparatory operations in the spacecraft’s SES and SB management, it is proposed to reduce the area of the SB that is adversely affected by the flow of these particles.

The technical result is achieved by the fact that in the method of controlling the position of the solar panels of the spacecraft, including turning the solar panels into a working position, providing the spacecraft with electric energy, corresponding to combining the normal to its illuminated working surface with the plane formed by the axis of rotation of the solar panels and the direction to The sun, measuring the density of the current flux of solar electromagnetic radiation, determining the time instant of the beginning of solar ac evidence, determining the time at which particles reach the high energies of the surface of the spacecraft, measuring the flux density of high-energy particles, comparing the measured flux densities of high-energy particles with threshold values, turning the solar panels at an angle between the normal to their illuminated working surface and the direction to the Sun, corresponding to the minimum area of impact of high-energy particle fluxes on the surface of solar cells while providing space apparatus with electric energy, at a time when the measured values of the flux density of high-energy particles exceed threshold values and the solar panels return to their working position at a time at which the flux-density of high-energy particles falls below threshold values, additionally determine the time of the appearance of precursors of the negative effects of particle fluxes high energies on the spacecraft, at the time of the appearance of precursors of the negative impact of particle fluxes of high energies of the spacecraft charge the batteries of the spacecraft’s power supply system to the maximum charge level, if the measured values of the high flux density of particle fluxes exceed the threshold values compared with them, they turn the solar panels to reach the angle between the normal to their illuminated working surface and direction to the sun _{s_min_AB} α corresponding to the minimum flow area exposure of high-energy particles on the surface hydrochloric echnyh batteries while providing the spacecraft with electricity from solar panels and rechargeable power supply system, determined by the relation:

α _{s_min_AB} = arccos (max {0, I _n -I _AB } / I _m ),

where I _n - load current from consumers of the spacecraft,

I _m is the maximum current generated when the illuminated working surface of the solar panels is oriented perpendicular to the sun's rays,

I _AB - current allowable discharge current of batteries

and the resulting shortage of electricity on board the spacecraft is compensated by the discharge of the batteries, while the charge level of the batteries is monitored, and upon reaching the minimum acceptable value of the charge level of the batteries, the current value of the permissible discharge current of the batteries is reset and the batteries are disconnected from the external load.

In addition, the task is solved in that in the control system for the position of the solar panels of the spacecraft, including a solar battery with four photovoltaic batteries installed on it, a device for turning the solar panels, an amplifying-converting device, a control unit for orienting the solar panels in the direction to the Sun, block turning the solar batteries to a predetermined position, two current regulators, a battery pack, a battery charger, omand for battery charge, load current sensor, power supply control unit, power supply bus, unit for measuring the density of the current solar electromagnetic radiation flux, unit for determining solar activity, unit for determining the moment of time of particle impact on the spacecraft, unit for measuring the density of high-energy particle fluxes, a unit for determining a time point for starting control of solar batteries by load currents, a control unit of solar batteries by load currents, wherein the solar battery through its first output, combining the outputs of two photovoltaic batteries, is connected to the first input of the solar rotator, and through the second output, combining the outputs of two other photovoltaic batteries, is connected to the second input of the solar rotator, and the outputs of the solar orientation control units in the direction to the Sun and turning the solar panels to a predetermined position are connected respectively to the first and second inputs of the amplifying-converting device, the output in turn, it is connected to the third input of the solar rotator, the first and second outputs of the solar rotator are connected to the inputs of the first and second current regulators, and the outputs of the current regulators are connected to the power supply bus of the spacecraft, the battery pack is connected by its input, through the battery charger, connected to the power supply bus, while the battery charger is connected by its first input to the specified bus, and a load current sensor is connected to the second input of the battery charger, which is connected, in turn, to the power supply bus, the battery pack is connected with its output to the first input of the battery charge command generation unit, and the first is connected to the second input of the specified unit the output of the control unit of the power supply system, the output of the unit for generating commands for charging batteries is connected to the third input of the battery charger, the second and third the th output of the power supply control unit is connected to the first inputs of the solar orientation orientation control units in the direction of the Sun and the solar panels in the set position, the third output of the solar panels rotation unit is connected to the second inputs of the solar unit orientation control units in the direction of the Sun and solar panels to a predetermined position, the output of the unit for measuring the density of the current solar electromagnetic radiation flux is connected to the input of the determination unit with activity, the first output of which, in turn, is connected to the input of the unit for determining the instant of time of particle impact on the spacecraft, the outputs of the unit for determining the instant of time of particle impact on the spacecraft and the unit for measuring high density particle flux density are connected to the first and second inputs of determining the timing of the start of controlling solar cells by load currents, and the input of the unit for measuring the density of fluxes of high-energy particles is connected to the second output of the unit determination of solar activity, the output of the unit for determining the time of the start of solar battery control by load currents is connected to the input of the power supply control unit, the fourth output of which, in turn, is connected to the first input of the solar control unit by load currents, the third input and output of which are connected to, respectively, the third output of the solar battery rotation device and the third input of the amplification-converting device, an additional unit for determining the required and from solar panels, a unit for determining the moments of time of the precursors of the negative impact of high energy particles on the spacecraft and a unit for setting acceptable values for the charge level of the batteries, while the first and second inputs and the output of the unit for determining the required current from the solar panels are connected to the second output of the current sensor, respectively load, the second output of the battery charger and the second input of the solar control unit for load currents, the outputs of the measurement unit the flow patterns of high-energy particle fluxes and the unit for measuring the density of the current solar electromagnetic radiation flux are also connected to the first and second inputs of the time determination block of the precursors of the negative impact of high-energy particles on the spacecraft, the output of which is connected to the second input of the power supply control unit, and the first and the second outputs of the unit for setting permissible values of the level of charge of the batteries are connected to, respectively, the third input of the battery ka forming commands to charge the batteries and the fourth input of the battery charger.

The essence of the proposed method is as follows.

The direct protective flap of the SB from the direction of the negative impact of high-energy particle fluxes is performed when the density of the high-energy particle fluxes exceeds some predetermined threshold values. At the same time, as the initial steps taken before the direct implementation of protective measures, continuous monitoring of the current state of near-Earth space and current solar activity is carried out and the fulfillment and non-fulfillment of the criteria for hazardous radiation conditions, in particular the criteria for monitoring solar activity developed by the National Oceanic and Atmospheric Administration (NOAA), are analyzed ) (see [12]). In this situation, when the criteria for an unconditional hazard have not yet been fulfilled, but the threshold of the previous hazard level has already been reached, they should be considered as situations that are “harbingers” of the considered negative impact.

When the precursors of the negative impact of high-energy particle flows on the spacecraft appear, they carry out the maximum charge of the AB SES spacecraft. This makes it possible in the future, when the measured values of the density of fluxes of high-energy particles exceed the threshold values compared with them, to turn the working surfaces of the SB panels away from the direction of the fluxes of these particles to the maximum possible angle, provided that the arising deficit of electricity on board the spacecraft is compensated by an AA discharge. Moreover, this value α _{s_min_AB of the} angle of the protective _{flap of} the SB is determined by the ratio:

where I _m is the maximum current generated when the illuminated working surface of the SB panels is oriented perpendicular to the sun's rays,

I _sat - the need of the current Council.

At the same time, the required current from SB I _SB is determined as the minimum required current that SB needs to generate to provide spacecraft consumers taking into account the possibilities of using BAB SES spacecraft energy (i.e., when compensating for the arising shortage of electricity on board the spacecraft due to discharge of the SES battery) based on the ratios:

or

where I _n - load current from spacecraft consumers,

I _AB - current maximum allowable discharge current of AB SES KA.

To implement the method, a system is proposed, shown in the drawing and containing the following blocks:

1 - SB, on a rigid substrate of the housing of which four photovoltaic batteries are located;

2, 3, 4, 5 - BF ₁ , BF ₂ , BF ₃ , BF ₄ ;

6 - UPSB;

7 - UPU;

8 - BUOSBS;

9 - BRBSP;

10, 11 - RT ₁ and RT ₂ ;

12 - BAB;

13 - ZRU AB;

14 - BFKZ AB;

15 - DTN;

16 - BUSES;

17 - SE;

18 - BIPEMI;

19 - BOSF;

20 - BOMVCH;

21 - BIPPCHVE;

22 - BOMVUSBTNZ;

23 - BUSBTNZ;

24 is a block for determining the moments of time of the precursors of the negative effects of high energy particles on the spacecraft (BOMVNPVCh),

25 - block determining the required current from solar panels (BOPTSB),

26 - block setting acceptable values for the level of charge of the batteries (BZDZUZSB).

In this case, SB (1) through its first output combining the outputs of BF ₁ (2) and BF ₄ (5) is connected to the first input of UPSB (6), and through a second output combining the outputs of BF ₂ (3) and BF ₃ ( 5), connected to the second input of UPSB (6). The outputs of the BUOSBS (8) and BRBSBZP (9) are connected respectively to the first and second inputs of the UPU (7), the output of which, in turn, is connected to the third input of the UPSB (6). The first and second outputs of UPSB (6) are connected respectively to the inputs PT ₁ (10) and PT ₂ (11), and the outputs PT ₁ (10) and PT ₂ (11) are connected to the ST (17). The BAB (12) is connected via its switchgear to the BAB (13) with the SE (17). At the same time, the switchgear switchgear (13) is connected with its first input to the specified bus, and the accident output (15) is connected to the second switchgear switchgear terminal (13), the input of which is connected, in turn, to the ШЭ (17). BAB (12) is connected by its output to the first input of the BFKZ AB (14), and the first output of the BUSES (16) is connected to the second input of the indicated unit. The output of the BFKZ AB (14) is connected to the third input of the indoor switchgear AB (13). The second and third outputs of the BUSES (16) are connected respectively to the first inputs of the BUSSBS (8) and BRSBZP (9). The third output of UPSB (6) is connected to the second inputs of the BUOSBS (8) and BRBSBZP (9). The output of BIPEMI (18) is connected to the input of the BOS (19). The first output of BOSF (19) is connected to the input of the BOMHF (20). The outputs of the BOMVVCH (20) and BIPPCHVE (21) are connected to the first and second inputs of the BOMVUSBTNZ block (22), respectively. The input BIPCHVE (21) is connected to the second output of the BOS (19). The output of the BOMVUSBTNZ (22) is connected to the first input of the BUSES (16). BUSES (16) is connected with its fourth output to the first input of BUSBTNZ (23). The third output of UPSB (6) is connected to the third input of BUSBTNZ (23). The output of the BUSBTNZ (23) is connected to the third input of the UPU (7). The first input BOPTSB (25) is connected to the second output of the DTN (15). The second input BOPTSB (25) is connected to the second output of the switchgear AB (13). The output of the BOPTSB (25) is connected to the second input of the BUSBTNZ (23). The output of the BIPCHVE (21) is connected to the first input of the BOMPVVVCH (24). The output of BIPEMI (18) is connected to the second input of BOMPVVVCH (24). The output of the BOMVPNVCH (24) is connected to the second input of the BUSES (16). The first and second outputs of the BZDZUZSB (26) are connected to the third input of the BFKZ AB (14) and the fourth input of the indoor switchgear AB (13), respectively.

The drawing also shows the dotted line mechanical connection of UPSB (6) with the body of the SB (1) through the output shaft of the battery drive.

In the power supply mode of the spacecraft, the system operates as follows. UPSB (6) serves for the transit transmission of electricity from SB (1) to PT ₁ (10) and RT ₂ (11). Voltage stabilization on the power supply bus of the SES is carried out by one of the RTs. At the same time, another RT is in a state with closed power transistors. The SB generators (1) (BF ₁ -BF ₄ ) operate in this case in the short circuit mode. When the load power becomes greater than the power of connecting the SB generators (1), another RT switches to voltage stabilization mode, and the energy of the idle generators is supplied to the power station of the SES. In certain periods, when the load power can exceed the power of the SB (1), the switchgear of the AB (13), due to the discharge of the AB block (12), it compensates for the shortage of electricity onboard the spacecraft. For these purposes, the AB switchgear (13) serves as an AB discharge regulator, which, in particular, monitors the battery charge level and, upon reaching the minimum acceptable value of the battery charge level, the value of which enters the battery switchgear (13) from the BZZUZSB (26), BAB (12) from external load. In this case, the switchgear switchgear (13), based on the current charge level of the battery, determines and supplies to its second output the current value of the permissible discharge current of the battery (in the mode of disconnecting the battery (12) from the external load, this value is zero).

In addition to the specified switchgear regulator AB (13) also contains a charge regulator AB. To conduct charge-discharge cycles in the indoor switchgear AB (13), information from DTN (15) is used. The charge of the BAB (12) is provided by the ZRU AB (13) through the BFKZ AB (14). For the case of metal-hydrogen AB, it is described in [5]. The bottom line is that the pressure sensors installed inside the batteries and the temperatures on the battery cases determine the density of hydrogen in the battery case. In turn, the hydrogen density determines the level of charge in the battery. When the hydrogen density in the battery is lower than the set level, a command is issued to charge it, and when the maximum density level is reached, to stop the charge. The indicated battery charge levels are regulated by commands from the BFKZ AB (14), while the values of the maximum allowable charge level of the AB are supplied to the BFKZ AB (14) with the BZDZUZB (26). Maintaining the battery in the maximum charged state negatively affects their state, and the battery is maintained in the current self-discharge mode, in which the battery’s charge operation is performed only periodically (for example, when controlling the Yamal-100 SES, once a few days, with a decrease in the charge level BAB at 30% of the maximum level).

Simultaneously with the operation in the spacecraft power supply mode, the system solves the problem of controlling the position of the planes of SB panels (1).

On command from BUSES (16), the BUOSBS unit (8) controls the orientation of the SB (1) to the Sun. BUOSBS (8) can be implemented on the basis of the spacecraft VESSEL (see [6]). In this case, the input information for the SB control algorithm is: the position of the unit direction vector on the Sun relative to the coordinate axes associated with the spacecraft, determined by the algorithms of the KIND kinematic contour; the position of the SB relative to the spacecraft body, obtained in the form of the current measured values of the angle α with the remote control of the UPS (6). The output of the control algorithm are commands for rotating the SB relative to the axis of the output shaft of the UPSB (6), and commands for stopping rotation. Remote control UPSB (6) give discrete signals about the position of the SB (1).

BIPEMI (18) measures the current flows of solar EMP and transmits them to BOS (19). In BOS (19), by comparing current values with given thresholds, the onset of solar activity is determined. By the command coming from the first output of the BOSFET (19) to the input of the BOMHF (20), the specified last block determines the time instant of the possible onset of exposure of high-energy particles to the spacecraft. From the second output of BOSF (19), through the input of BIPCHVE (21), a command is issued to start measuring the flux density of high-energy particles.

From the output of BIPCHCHE (21), the measured value of the flux density of high-energy particles is transmitted to the first input of the BOMVPNVCh (24) and to the second input of the BOMVUSBTNZ (22). At the second input of the BOMPNVCH (24) from the output of the BIPEMI (18), the measured values of the current fluxes of solar EMP are supplied.

In BOMVPNVCh (24), the dynamics of changes in the density of fluxes of particles of high energies is estimated and situations that can be considered as precursors of the negative effect of particles on the spacecraft are revealed. Such situations are the excess of the specified critical values by the measured flux density of high-energy particles in the presence of a tendency to its further increase. When identifying and identifying such situations, the data of solar EMR fluxes obtained from BIPEMI are also used (18). When registering in the BOMVPNVCH (24) such precursor situations, a signal is generated at the output of this unit, which is fed to the second input of the BUSES (16).

By a command at the second input of the BUSES (16), this unit gives a command to the BFKZ AB (14), by which this unit charges the BAB (12) to the maximum charge level through the switchgear AB (13). Moreover, for the case of metal-hydrogen batteries (see [5]), the pressure sensors installed inside the batteries and the temperatures on the battery cases determine the hydrogen density in the battery case, which determines the charge level of the batteries. When the maximum density level is reached, a command to terminate the charge is issued.

The BOPTSB inputs (25) from the second outputs of the DTN (15) and ZRU AB (13) receive the current values of the load current from the spacecraft consumers I _n and the permissible discharge current AB I _AB . Using these BOPTSB values (25), using the relations (4), (5), determines the value of I _SB - the current minimum acceptable value of the required current from the SB (taking into account the possibility of consumers using energy from the BAB (12)), and gives it to the second input BUSBTNZ (23).

Information about the time instant of the possible onset of particle impact on the spacecraft is transmitted from the output of the BOMVCH (20) to the BOMVUSBTNZ (22) through its first input. In BOMVUSBTNZ (22), an actual assessment of the negative impact of the PFV is carried out by comparing the current measured value of the exposure characteristic with threshold values, starting from the time determined by the BOMVHF (20). A necessary condition for receiving a command at the output of the BOMVUSBTNZ (22) is the presence of two signals - from the outputs of the BOMVVCh (20) and BIPPCHVE (21).

When the BOMVUSBTNZ (22) issues a command to the first input of the BUSES (16), this unit generates a command at its fourth output, which connects the BUSBTNZ to the control SB (23).

BUSBTNZ (23) determines the angle α _{s_min_AB} by expression (3). To calculate the indicated angle, the current value of the required current from the SB obtained from the BOPTSB is used (25). In addition, with the remote control of the UPSB (6), information about the current value of the angle of rotation of the SB α is received in the indicated block. Having determined the value of the angle α _{s_min_AB} , the algorithm laid down in the BUSBTNZ (23) compares it with the current value of the angle α and calculates the mismatch angle between α and α _{s_min_AB} and the necessary number of control pulses to activate the SB control drive (1). Control pulses are transmitted to the UPA (7). After converting and amplifying the indicated pulses into the UPA (7), they arrive at the input of the UPSB (6) and drive the drive.

When the BOMVUSBTNZ (22) does not issue a command to the first input of the BUSES (16), this block, depending on the flight program being performed by the spacecraft, transfers control of the SB (1) to one of the blocks of the BUOSES (8) and the BRSBZP (9).

The operation of the FSBS (8) is described above.

BRRSBZP (9) controls SB (1) according to program settings. The SB control algorithm (1) according to the program settings allows you to install the battery in any given position α = α _z . At the same time, information from the remote control of the UPSB (6) is used to control the turning angle in the BRBSBZP (9).

Implementation of BOMVUSBTNZ (22) and BOMVPNVCH (24) is possible both on the basis of hardware and software of the MCC KA, and on board the KA. At the outputs of BOMVUSBTNZ (22) and BOMVPNVCh (24), respectively, the commands “start control SB on load currents” and “start control SES in the mode of preparation for the negative impact of high-energy particles on the spacecraft”, which enter the BUSES (16), are formed, respectively In this case, the last command is functionally perceived by the BUSES (16) as a command to execute the battery charge to the maximum charge level.

An example of the implementation of the BUSES (16) can be provided by the radio service channel of the control channel (SCU) onboard systems of the spacecraft "Yamal-100", consisting of an earth station (ES) and airborne equipment (BA) (see description in [10, 11]). In particular, the BA SKU together with the ZS SKU solves the problem of issuing to the on-board digital computer system (BCVS) the spacecraft digital information (DI) and its subsequent acknowledgment. The BCVS, in turn, manages the BUOSBS units (8), BRBSPZ (9), BUSBTNZ (23), and BFKZ AB (14).

In this implementation of BUSES (16), the interaction of BA SKU in terms of the exchange of digital information is carried out via the main exchange channel (MCO) in accordance with the MIL-STD-1553 interface. As a BCVS subscriber, a device is used - a conjugation unit (BS) from the BA SKU. The processor BCVS periodically makes surveys of the state of the BS to determine the availability of the data packet. If the packet is available, the processor begins data exchange.

The UPU (7) plays the role of an interface between the BUSSBS (8), BRSBZP (9), BUSBTNZ (23) and UPSB (6) and serves to convert digital signals to analog and amplify the latter.

BUSBTNZ (23) is a spacecraft onboard unit, teams to which come from BUSES (16). Implementation of BUSBTNZ (23), BOPTSB (25), BZDZUZSB (26) can be carried out on the basis of the SCVS spacecraft (see [6], [8]).

Thus, an example of the implementation of the fundamental blocks of the system is considered.

We describe the technical effect of the proposed inventions.

The proposed technical solutions reduce the negative impact of high-energy particle fluxes on the working surface of the SB at the moments of the regime of “protective” flap of the SB from the direction to the Sun. This is achieved by reducing the area of the SB working surface, which is negatively affected by the flows of these particles, by maximizing the angle of rotation of the normal to the SB working surface from the direction to the Sun, while ensuring that the spacecraft is provided with electricity. The maximization of the angle of the lapel is achieved by the fact that the SES of the spacecraft is brought into the state of maximum charge of the battery in advance, which makes it possible to realize the maximum possible angle of the "protective" lapel of the Security Camera from the direction to the Sun. Considering, for example, that when controlling a Yamal-100 spacecraft’s SES after an AB charge operation to a maximum level, the increase in the possible discharge current of the AB is about 30%, then the corresponding increase in the angle of the “protective” flap of the SB and, as a result, the decrease in the negative impact of particle flows high energies on the working surface of the SB is a significant amount.

LITERATURE

1. Eliseev A.S. Space Flight Technique. Moscow, "Engineering", 1983.

2. Rauschenbach G. Handbook for the design of solar panels. Moscow, Energoatomizdat, 1983.

3. Flight rules when performing joint operations of the Shuttle and the ISS. Tom S. Flight Operations Management. Space Center named after Lyndon B. Johnson. Houston, Texas, Basic Edition, 8/8/2001.

4. Spacecraft power supply system. Technical description. 300GK.20Yu. 0000-ATO. RSC Energia, 1998.

5. Center B.I., Lyzlov N.Yu., Hydrogen-metal electrochemical systems. Leningrad. "Chemistry", Leningrad Branch, 1989.

6. The motion control and navigation system of the spacecraft. Technical description. 300GK.12YU. 0000-ATO. RSC Energia, 1998.

7. Halperin Yu.I., Dmitriev A.V., Zeleny L.M., Panasyuk L.M. The effect of space weather on the safety of aviation and space flights. Flight 2001, pp. 27-87.

8. Engineering reference for space technology. Publishing House of the Ministry of Defense of the USSR, M., 1969.

9. Griliches V.A., Orlov P.P., Popov L.B. Solar energy and space travel. Moscow, "Science", 1984.

10. Earth station service channel control spacecraft "Yamal". Manual. ZSKUGK.0000-ORE. RSC Energia, 2001.

11. On-board equipment of the service control channel of the spacecraft "Yamal". Technical description. 300GK.15YU. 0000A201-OTO. RSC Energia, 2002.

12. Kovtun B.C., Soloviev S.V., Zaikin S.V., Gorodetsky A.A. A method for controlling the position of solar panels of a spacecraft and a system for its implementation. RF patent 2242408 for application 2003108114/11 of 03.24.2003.

Claims (2)

1. A method of controlling the position of the solar panels of a spacecraft, including turning the solar panel panels into a working position, providing the spacecraft with electricity and corresponding to combining the normal to their illuminated work surface with the plane formed by the axis of rotation of the solar panels and the direction to the Sun, measuring the current density the flux of solar electromagnetic radiation, determining the time instant of the onset of solar activity, determining the time instant life of high-energy particles on the surface of the spacecraft, measuring the density of high-energy particle fluxes, comparing the measured values of the high-energy particle flux densities with threshold values, turning solar panels at an angle between the normal to their illuminated work surface and the direction to the Sun, corresponding to the minimum area of the effects of the fluxes high-energy particles on the surface of solar panels while providing the spacecraft with electricity at a time thresholds and return of the solar panels to the operating position at a point in time at which the density of high-energy particle fluxes falls below threshold values, characterized in that they additionally determine the time moments of the appearance of precursors of the negative effects of high-energy particle fluxes to the spacecraft and at the indicated times, charge the batteries of the space power supply system of the apparatus to the maximum charge level, if the measured values of the flux density of high-energy particles exceed the threshold values compared with them, the solar panels are rotated until the angle between the normal to their illuminated working surface and the direction α _{s_min_AB is} directed to the Sun, corresponding to the minimum area of flux impact high-energy particles on the surface of solar panels, while providing the spacecraft with electricity from solar and battery x batteries of the power supply system, and determined by the ratio α _{s_min_AB} = arccos (max {0, I _n -I _AB } / I _m ), where I _n is the load current of the spacecraft consumers; I _m is the maximum current generated when the illuminated working surface of the solar panels is oriented perpendicular to the sun's rays; I _AB - the current allowable discharge current of the batteries, and the resulting shortage of electricity on board the spacecraft is compensated by the discharge of the batteries, while the charge level of the batteries is monitored and, upon reaching the minimum acceptable value of this level, the current value of the allowable discharge current of the batteries is reset and produce disconnecting batteries from an external load. 2. The control system for the position of the solar panels of the spacecraft, consisting of four photovoltaic solar panels mounted on the panels, including a device for turning the indicated solar panels, an amplifying-converting device, a control unit for orienting the solar batteries in the direction toward the Sun, a unit for turning the solar batteries to a predetermined position, two current regulators, a battery pack, a battery charger, a battery charge generation unit batteries, load current sensor, power supply control unit, power supply bus, unit for measuring the density of the current flow of solar electromagnetic radiation, unit for determining solar activity, unit for determining the time of exposure of high-energy particles to the spacecraft, unit for measuring the density of high-energy particle fluxes, determination unit the time of the start of solar battery control by load currents, the solar control unit by load current, while the solar ba Area through its first output, combining the outputs of two photovoltaic batteries, is connected to the first input of the solar rotator, and through the second output, combining the outputs of two other photovoltaic batteries, is connected to the second input of the solar rotator, and the outputs of the solar orientation control units are direction to the Sun and turning solar panels to a predetermined position are connected, respectively, with the first and second inputs of the amplifying-converting device, the output of which, in in turn, it is connected to the third input of the solar rotator, the first and second outputs of the solar rotator are connected respectively to the inputs of the first and second current regulators, and the outputs of the current regulators are connected to the power supply bus of the spacecraft, the battery pack is connected to its input via the charger for batteries, connected to the power supply bus, while the battery charger is connected with its first input to the specified bus, and to the second a load current sensor is connected to the input of the battery charger, which is connected, in turn, to the power supply bus, the battery pack is connected with its output to the first input of the battery charge command generation unit, and the first output of the control unit is connected to the second input of the indicated block power supply system, the output of the unit for generating commands for charging batteries is connected to the third input of the battery charger, the second and third outputs b the control panel of the power supply system is connected to the first inputs of the solar orientation orientation control units in the direction of the Sun and turning the solar batteries to a predetermined position, the third output of the solar panel rotation control units is connected to the second inputs of the solar orientation control units for the solar direction and turning of the solar batteries to the specified position, the output of the unit for measuring the density of the current flow of solar electromagnetic radiation is connected to the input of the unit for determining the solar act in fact, the first output of which, in turn, is connected to the input of the unit for determining the moment of time of particle impact on the spacecraft, the outputs of the unit for determining the moment of time of particle impact on the spacecraft and the unit for measuring the density of high-energy particle fluxes are connected to unit for determining the time instant for the start of control of solar cells by load currents, and the input of the unit for measuring the density of fluxes of high-energy particles is connected to the second output of the unit for determining solar activity, the output of the unit for determining the time of the start of solar battery control by load currents is connected to the input of the power supply control unit, the fourth output of which, in turn, is connected to the first input of the solar battery control unit by load currents, the third input and output of which are connected to , respectively, to the third output of the rotation device of the solar batteries and the third input of the amplification-converting device, characterized in that it further includes a unit for determining the required current from the solar batteries, the unit for determining the moments of the appearance of precursors of the negative impact of high energy particles on the spacecraft and the unit for setting the acceptable values of the charge level of the batteries, while the first and second inputs and output of the unit for determining the required current from the solar panels are connected to, respectively, the second output of the load current sensor, the second output of the battery charger and the second input of the solar control unit for the load currents, output The odes of the unit for measuring the density of the flux of particles of high energies and the unit for measuring the density of the current flux of solar electromagnetic radiation are also connected, respectively, with the first and second inputs of the unit for determining the moments of time of the precursors of the negative effects of high-energy particles on the spacecraft, the output of which is connected to the second input of the control unit of the power supply system , and the first and second outputs of the unit for setting the permissible values of the charge level of the batteries are connected, respectively about with the third input of the unit for generating commands for charging batteries and the fourth input of the battery charger.