RU2784977C1 - Method for assessing the efficiency of solar batteries in the power supply system of a vehicle, mostly space - Google Patents

Abstract

FIELD: technology.

SUBSTANCE: invention relates to the field of technology, mainly space, and in particular to power supply systems (PSS) of vehicles, mainly space, and can be used in the operation of their solar panels (SP). The method for evaluating the efficiency of the SP of the PSS of an apparatus, mainly a space one, includes turning the SP, measuring the current of the SP and determining the current value of the light flux from the Sun and the angles of its incidence on the SP. At the selected time intervals, the apparatus is deployed until the full illumination of the front and rear surfaces of the SP, respectively, by the Sun. On the other 2n-2 time intervals, n≥2 - the number of SBs, the apparatus is deployed until different SP surfaces are fully illuminated by the Sun. The measurement of the total current of the SP is performed at the moments of their full illumination at time intervals when the points of intersection of each of the planes in which the SP lie with the surface of the external environment, visible from the SP, are shaded from the Sun. The efficiency of a separate SP is estimated by the current values generated by the SP when its front and rear surfaces are illuminated, respectively, with solar radiation of the reference brightness along the normal to the SP surface.

EFFECT: invention increases the accuracy of the evaluation during implementation.

1 cl, 1 dwg

Description

The invention relates to the field of technology, mainly space, namely to power supply systems (PSS) of vehicles, mainly space, and can be used in the operation of their solar panels (SB).

One of the components of monitoring the current performance of the PSS SS, including spacecraft (SC), is the control of the main electrical characteristics of the SB - the output current, voltage and power of the SB. At the stage of design and manufacture of the SB, a theoretical calculation of the output parameters of the SB is carried out, which can be based on the method of moving the current-voltage characteristic, taking into account various influences of the environment and load parameters on the characteristics of the SB (SC power supply system. Technical description. 300GK.20Yu.0000- ATO, RSC Energia, 1998; Raushenbakh, G. Reference book on the design of solar batteries, Moscow, Energoatomizdat, 1983, pp. 49, 54).

The disadvantage of this method for monitoring the current performance of the SB is that the models of space flight factors used in the calculations have limited accuracy, which does not allow obtaining reliable data on the real characteristics of the SB in flight, taking into account the degradation process of the SB.

To control the actual characteristics of the SB in flight, measurement data of the actual output current of the SB, generated by photoelectric converters (PVC) under the influence of solar radiation, are used, while the SB are set in such a way that the luminous flux arrives perpendicular to the working surface of the SB (Eliseev A.S. Space flight technology Moscow, "Mashinostroenie", 1983, pp. 190-194; Raushenbakh G. Reference book on the design of solar batteries. Moscow, Energoatomizdat, 1983. p. 57; RF patent No. 2353555 on application No. 2006131395, priority dated 08.31.2006), why the SB is deployed to the working position corresponding to the alignment of the normal to their illuminated working surface with the direction to the Sun, and the control of the current SB performance is carried out based on the results of comparing the measured current values with the specified values - the current SB efficiency is estimated by the ratio of the measured actual output parameters of the SB to their nominal values - design or some reference values, for example, those measured during previous flight stages.

The choice of current strength as a controlled output characteristic of the SB is due to the fact that its strength is a variable directly dependent on the state of the SB as a whole, and the voltage is a fairly stable value and is determined mainly by the physical properties of the photoelectric converters used for the manufacture of the SB, while the operating mode FEP at the design stage of the SB is set in such a way that the generated power (as the product of current and voltage) is the maximum possible.

This method provides control over the effectiveness of the SA during the flight of the spacecraft. Smaller values of the actual output currents of the SB in relation to the specified design or initial values mean degradation of the SB. The disadvantage of this method is that it does not provide for the measurement of the SB current under the same external flight conditions, which is necessary to justify further comparison of the results of the measurements.

между направлением на Солнце и нормалью к плоскости орбиты КА, при этом на витках, на которых достигает локального минимума модуль угла

где λ^* - угол между нормалью к плоскости орбиты и нормалью к рабочей поверхности СБ в фиксированном положении СБ, в котором нормаль к рабочей поверхности СБ составляет острый угол с направлением полета и отстоит от направления в надир на угол, ближайший к сумме углов Q_z+Q_a+Q_s, в поддерживаемой ориентации КА; Q_z и Q_s - значения угловых полурастворов видимых с КА дисков Земли и Солнца, соответственно; Q_a - угол возвышения верхней границы атмосферы над видимым с КА горизонтом Земли; фиксируют измеренное значение тока СБ I и определяют на момент измерения тока значение расстояния от Земли до Солнца D_I и значение угла между нормалью к рабочей поверхности СБ и направлением на Солнце α_I, в ходе полета повторяют вышеописанные действия и оценку состояния СБ непосредственно по началу светового участка орбиты выполняют по результатам сравнения полученных на текущем и на предыдущих этапах полета значений контрольного параметра, определяемого по формуле, где D_cp -

среднее расстояние от Земли до Солнца.A known method for assessing the state of the SB spacecraft with inertial actuators (RF patent No. 2655089 according to the application No. 2017104052, priority dated 02.07.2017 - prototype), including the orientation of the SB with the normal to the working surface on the Sun, measuring the SB current and assessing the state of the SB based on the results of comparing the values current measured at the current and previous stages of flight, according to which the construction and maintenance of the orientation of the spacecraft in the orbital coordinate system is carried out, at which the external disturbing moment per revolution that affects the spacecraft reaches a minimum value, the SB is sequentially turned into fixed positions, the current one of which is selected from the condition minimization of the angle between the normal to the working surface of the SB and the direction to the Sun, on successive turns of the orbit at the moments of touching the upper boundary of the Earth’s atmosphere by the disk of the Sun visible from the spacecraft at sunrise, the values of the SB current and angle are measured

between the direction to the Sun and the normal to the plane of the SC orbit, while on the turns, on which the angle module reaches a local minimum

where λ ^* is the angle between the normal to the plane of the orbit and the normal to the working surface of the SB in a fixed position of the SB, in which the normal to the working surface of the SB makes an acute angle with the direction of flight and is separated from the direction to the nadir by an angle closest to the sum of the angles Q _z + Q _a +Q _s , in the supported orientation of the spacecraft; Q _z and Q _s are the values of the angular half-openings of the disks of the Earth and the Sun visible from the spacecraft, respectively; Q _a - elevation angle of the upper boundary of the atmosphere above the horizon of the Earth visible from the spacecraft; the measured value of the SB current I is fixed and at the time of current measurement the value of the distance from the Earth to the Sun D _I and the value of the angle between the normal to the working surface of the SB and the direction to the Sun α _I are determined, during the flight the above actions are repeated and the assessment of the state of the SB directly at the beginning of the light segment of the orbit is performed based on the results of comparing the values of the control parameter obtained at the current and previous stages of flight, determined by the formula, where D _cp -

the average distance from the earth to the sun.

This method ensures minimization of the influence of illumination from the Earth when assessing the state of the SB based on the results of direct measurement of the SB current directly at the beginning of the light section of the orbit against the background of a regular flight of a spacecraft with inertial actuators in the base (duty) orientation.

The disadvantage of the prototype method is due to the fact that it does not provide the conditions for evaluating the efficiency of a separate solar battery based on data on the total current of the solar cells of the SEP, obtained during the modes for evaluating the efficiency of the solar cells of the SEP.

The problem to be solved by the present invention is the creation of conditions for a highly accurate assessment of the efficiency of solar cells of the SEP of vehicles, mainly space ones.

The technical result achieved by the implementation of the present invention is to increase the accuracy of estimating the efficiency of solar cells according to the total current of the solar cells of the SPS by determining the performance of each of the surfaces - both front and rear - of each solar cell of the SPS.

The technical result is achieved by the fact that in the method for assessing the efficiency of solar batteries of the power supply system of a predominantly spacecraft, including turning the solar panels to positions determined from the condition of minimizing the value of the angle between the normal to the front surface of the solar battery and the direction to the Sun, measuring the total current of the solar panels and determining the current value of the luminous flux from the Sun and the angles of its incidence on the plane of the surface of the solar panels, unlike the prototype, at one time interval, the device is deployed on which the solar panels are installed / placed, until the solar panels are fully illuminated by the Sun at angles between the direction to the Sun and normals to the front surfaces of the solar panels is less than a given acute angle, on another time interval, the specified device is deployed until the solar panels are fully illuminated by the Sun and the solar panels are rotated to a position at which the angles between the direction to Sun and normals to the rear surfaces of the solar panels are less than a given acute angle, on other 2n-2 time intervals, where n, n≥2 is the total number of solar panels, turn the indicated device until the solar panels are fully illuminated by the Sun and rotate less than n solar panels to the position at which the angles between the direction to the Sun and the normals to the rear surfaces of the solar panels are less than the specified acute angle, provided that for each solar battery of the power supply system at least one time interval the front side of the solar battery is facing the Sun and at least At one time interval, the back side of the solar battery is facing the Sun, the measurement of the total current of the solar panels is performed at the described moments of their full illumination at time intervals when the points of intersection of each of the planes in which the solar panels lie with the surface of the external environment, visible from the solar panels , are shaded from the Sun, and determine the component of the measured current from the illumination of solar panels with a light flux other than solar does not exceed the current measurement error, and the efficiency of an individual solar battery is estimated by the current values generated by the solar battery when its front and back surfaces are illuminated, respectively, with solar radiation of the reference brightness along the normal to the surface solar batteries, which are determined by measurements of the total current of solar batteries, performed on the mentioned 2n time intervals during the specified time intervals, taking into account the current value of the light flux from the Sun and the angles of its incidence on the surface of the solar batteries.

The essence of the invention is illustrated by a drawing, which shows a diagram explaining the definition of the intersection points of the line of the Earth's horizon visible from the spacecraft with the planes in which the solar panels lie. The following designations are introduced in the drawing:

O - the center of the Earth;

A - solar panels SEP KA;

S - direction to the Sun;

- нормаль к лицевой поверхности первой солнечной батареи;

- normal to the front surface of the first solar battery;

- нормаль к лицевой поверхности второй солнечной батареи;

- normal to the front surface of the second solar battery;

γ - given acute angle;

1 - shadow part of the Earth's surface;

2 - the line of the horizon of the Earth visible from the spacecraft;

3 - planes in which solar batteries lie;

4 - points of intersection of the line of the Earth's horizon visible from the spacecraft with the planes in which the solar batteries lie (these points are located on the shadow part of the Earth's surface).

Let us explain the actions proposed in the method using the example of evaluating the efficiency of solar batteries of the spacecraft power supply system.

On many spacecraft, the EPS of the spacecraft includes solar batteries with two-way light sensitivity and one current sensor, through which the measurement and receipt of telemetric information (TMI) of the total current of all solar batteries is carried out.

As a rule, the solar array position control system of the spacecraft EPS provides for setting the solar arrays to predetermined discrete positions fixed in the coordinate system associated with the spacecraft, and the rotation of the solar arrays between such positions is performed at a given angular velocity of the solar arrays. At the same time, to perform various flight operations, various solar array orientation control modes are provided, including the mode of automatic guidance of solar arrays (tracking) to the Sun and the mode of setting solar arrays to a predetermined position (the position is selected from the list of the above-mentioned preset discrete positions of solar arrays fixed in coordinate system associated with the spacecraft). At the same time, in the mode of automatic guidance of the solar panels (tracking) to the Sun, the control system automatically selects the moment of the start of the rotation of the solar panels to transfer the solar panels from the current fixed position to the next one.

Thus, at an arbitrary current moment in time, the solar panels are either in one of the fixed positions (in this case it is the current discrete fixed position) or in the process of transition between two discrete fixed positions. At the same time, in the mode of automatic guidance of solar panels (tracking) to the Sun, the moments when the battery is in one of the discrete positions are determined by measurements of the current orientation of the spacecraft and measurements of the position of the Sun by determining the moments of the beginning and end of the rotation of the solar panels, taking into account the logic of automatic control of solar panels in this mode .

In the proposed technical solution to solve the problem, the current value of the distance from the Earth to the Sun is determined, and the current value of the light flux of solar radiation in the orbit of the spacecraft is determined from a certain current distance from the Earth to the Sun.

At one time interval - for example, a selected orbit turn - the spacecraft is deployed until the solar panels are fully illuminated by the Sun at angles between the direction to the Sun and the normals to the front surfaces of the solar panels that are less than a given acute angle.

Turning the spacecraft until the solar arrays are fully illuminated by the Sun ensures that the shading of the photoelectric converters (PVCs) placed on the surface of the solar arrays by the spacecraft structural elements is excluded.

The illumination of the solar arrays by the Sun, necessary for the normal operation of the SEP, is provided by the rotation of the solar arrays to positions determined from the condition of minimizing the angle between the normal to the front surface of the solar array and the direction to the Sun. This position of each solar battery can be described by the condition

where α _faces - the value of the angle between the direction to the Sun and the normal to the front surface of the solar battery; γ is a given acute angle.

At another time interval - for example, another orbital turn - the spacecraft is deployed until the solar panels are fully illuminated by the Sun and the solar panels are rotated to a position at which the angles between the direction to the Sun and the normals to the rear surfaces of the solar panels are less than a given acute angle - i.e. each solar panel is rotated to a position where the condition is met

where α _rear - the value of the angle between the direction to the Sun and the normal to the rear surface of the solar battery; γ is a given acute angle.

Turning the spacecraft until the solar batteries are fully illuminated by the Sun ensures that the rear side of the solar battery is not shaded by the elements of the spacecraft structure.

On each of the other k=2n-2 time intervals - for example, orbit turns, - where n=2, 3, ... - the total number of solar panels, turn the spacecraft until the solar panels are fully illuminated by the Sun and turn m, m<n solar panels to the position at which the angles between the direction to the Sun and the normals to the rear surfaces of the solar panels are less than the specified acute angle, provided that for each solar battery of the power supply system at least in one time period (orbital orbit) the front side of the solar battery is facing the Sun and at least on one time interval (orbital orbit) the back side of the solar battery is facing the Sun.

For example, in the case when the SC SEP contains n=2 solar arrays, on k=2 turns of the orbit, these solar arrays are oriented as follows:

- on one turn, one (m=1) solar battery is rotated to a position at which the angle between the direction to the Sun and the normal to the rear surface of this solar battery is less than the specified acute angle.

- on another turn, another (m=1) solar battery is rotated to a position at which the angle between the direction to the Sun and the normal to the back surface of this solar battery is less than the specified acute angle.

Thus, on these k=2 turns, the following condition is fulfilled: for each solar battery of the SC SEP, on at least one turn (in this case, on one) the front side of this solar battery is facing the Sun and on at least one turn (in in this case - on one) the back side of this solar battery is facing the Sun.

The measurement of the total current of solar panels is performed at the described moments of their full illumination at time intervals when the points of intersection of each of the planes in which the solar panels lie with the surface of the external environment, visible from the solar panels, are shaded from the Sun (i.e. - as applied to the EPS of the spacecraft - when the points of intersection of the line of the horizon of the Earth visible from the spacecraft with the planes in which the solar panels lie are located on the shadow part of the Earth's surface), and the determined component of the measured current from the illumination of the solar panels with a light flux different from the solar one (i.e. - in relation to the SEP SC - by the light flux leaving the Earth) does not exceed the current measurement error.

Thus, measurements of the total current of solar panels are performed on the considered 2n orbit turns (2n=1+1+k) during time intervals when both of the following conditions are met:

- the points of intersection of the line of the Earth’s horizon visible from the spacecraft with the planes in which the solar batteries lie, are located on the shadow part of the Earth’s surface front surfaces of solar cells and condition (1) is satisfied.

- the current measured value of the total current of the solar panels does not exceed the set value, determined from the condition that the determined (calculated taking into account the TMI data of the current of the solar panels) component of the current measured current of the solar panels from the illumination of the solar panels by the luminous flux leaving the Earth does not exceed the current measurement error - those. component of the current generated by the specified illumination, ≤d, where d is the current measurement error).

The efficiency of each individual solar battery is estimated by the following values:

i - порядковый номер солнечной батареи);- the value of the current generated by the solar battery when its front surface is illuminated by solar radiation of the reference brightness along the normal to the surface of the solar battery (parameter

i - serial number of the solar battery);

, i - порядковый номер солнечной батареи);- the value of the current generated by the solar battery when its rear surface is illuminated by solar radiation of the reference brightness along the normal to the surface of the solar battery (parameter

, i - serial number of the solar battery);

,

, i=1, …, n используются измеренные значения суммарного тока солнечных батарей, полученные в описанных 2n сеансах измерений, которые отличаются один от другого комбинациями обращенных к Солнцу лицевых и тыльных сторон солнечных батарей, что, в общем случае, необходимо и достаточно для решения данной задачи.These values are determined by measurements of the total current of the solar cells, performed on the considered 2n time intervals (orbit turns) during the specified time intervals, taking into account the current value of the light flux from the Sun and the angles of its incidence on the plane of the surface of the solar cells. Namely, to determine the indicated 2n parameters

,

, i=1, …, n, the measured values of the total current of the solar cells are used, obtained in the described 2n measurement sessions, which differ from one another by combinations of the front and back sides of the solar cells facing the Sun, which, in the general case, is necessary and sufficient for solving this task.

,

, характеризующие эффективность, соответственно, лицевой и тыльной поверхности i-й солнечной батареи, можно определить как произведение площади лицевой/тыльной поверхности данной солнечной батареи на коэффициент генерации тока при освещении соответствующей (лицевой и тыльной) поверхности данной солнечной батареи солнечным излучением эталонной яркости по нормали к поверхности солнечной батареи. Указанные коэффициенты генерации тока определяются из соответствия измеренных значений суммарного тока солнечных батарей его расчетным модельным значениям, а именно из условия минимизации отличия расчетных модельных значений суммы токов всех солнечных батарей от данных ТМИ суммарного тока солнечных батарей (поскольку расчетные модельные значения тока каждой i-ой солнечной батареи являются функциями указанных параметров

,

). Задачу минимизации сформулированного функционала решаем с использованием известных математических методов, описанных, например, в книге Гилл Ф., Мюррей У., Райт М. Практическая оптимизация: Пер. с англ. - М.: Мир, 1985. - 509 с.For example, parameters

,

characterizing the efficiency of the front and rear surfaces of the i-th solar battery, respectively, can be defined as the product of the front/rear surface area of this solar battery by the current generation coefficient when the corresponding (front and back) surface of the given solar battery is illuminated by solar radiation of the reference brightness along the normal to the surface of the solar array. The indicated current generation coefficients are determined from the correspondence of the measured values of the total current of the solar panels to its calculated model values, namely, from the condition of minimizing the difference between the calculated model values of the sum of the currents of all solar panels and the TMI data of the total current of the solar panels (since the calculated model values of the current of each i-th solar batteries are functions of the specified parameters

,

). We solve the problem of minimizing the formulated functional using well-known mathematical methods described, for example, in the book Gill F., Murray W., Wright M. Practical optimization: Per. from English. - M.: Mir, 1985. - 509 p.

We note that the presence among the mentioned 2n different (unique) combinations of front and back sides of solar cells facing the Sun, a combination in which the back sides of all solar cells face the Sun (a loop on which condition (2) is satisfied), provides obtaining maximum accuracy in determining the efficiency parameters of the back surface of solar panels (since it is with such a combination of the sides of solar panels facing the Sun that the maximum accuracy is ensured in isolating the current from the total current of solar panels, which is generated from the illumination of the back side of one solar battery by the Sun).

The use of solar cell current measurements performed at the described position of the solar cells and at the specified time interval reasonably ensures the minimization of the influence of the illumination from the Earth on the generation of the current of solar cells with two-sided photosensitivity, namely, this minimization is achieved due to the fact that the contribution of the illumination from the Earth to the generated the current of solar cells, determined by the magnitude of the current component generated by illuminating the solar cells with the light flux leaving the Earth, is so small that it does not exceed the error in measuring the current of the solar cells, which means that it can be justifiably neglected and taken into account by approximate calculation models without loss of accuracy the resulting solution. In turn, this minimizes (eliminates) the inaccuracy/inaccuracy caused by this backlight in determining the values of the considered parameters for evaluating the efficiency of solar batteries by TMI of the solar battery current.

The described rotation of the solar arrays to a position in which the points of intersection of the line of the Earth’s horizon visible from the spacecraft with the planes of the solar arrays are located on the shadow part of the Earth’s surface ensures that in this position only one side of the solar arrays surface is illuminated - either the front or back - if the luminous flux (from the Sun and from the Earth illuminated by the Sun) enters one surface of the solar battery, then no luminous flux enters the other surface of the solar battery.

The choice of orbits for the implementation of the proposed actions can be carried out from the condition of the best opportunities for constructing the required orientation of the spacecraft and SB relative to the direction to the Sun. For example, the possibility of constructing the required orientation of the SC and SB can be determined by such a parameter as the angle between the direction to the Sun and the plane of the SC orbit - in this case, to implement the proposed actions, orbits are selected at which the angle between the direction to the Sun and the plane of the SC orbit is within the required ( specified) limits.

The orbits under consideration can either constitute a continuous sequence or be selected at intervals between individual orbits (this case can be realized, for example, when the restrictions imposed by the spacecraft flight plan do not allow the construction of the required orientation of the spacecraft and SB, in particular, the turn of the front surface of the SB from of the Sun, - in a row on successive revolutions of the spacecraft's orbit).

The proposed technical solution makes it possible to evaluate the efficiency of the SB both at the maximum steady-state operating temperature of the SB and at their minimum temperature.

Evaluation of SB efficiency at their minimum temperature is carried out by measurements of the total current of solar panels, performed immediately after the end of the zone of natural shading of solar panels from the Sun by the Earth (immediately at the beginning of the zone of illumination of solar panels by the Sun). In the case of evaluating the efficiency of the SB of the SC HSS, this condition corresponds to measurements of the SB current at the beginning of the light sections of the orbital turns of the SC.

Evaluation of the solar panels efficiency at their maximum steady-state operating temperature is carried out by measuring the total current of the solar panels, performed no earlier than a specified time value dT* after the beginning of the solar panels illumination zone by the Sun (the dT* value is determined from the condition that the solar panels reach a stable temperature mode of operation) . In the case of evaluating the efficiency of the SB of the SC HSS, this condition corresponds to measurements of the SB current at the end of the light segments of the orbital turns of the SC.

Let us describe the technical effect of the proposed invention.

The proposed technical solution improves the accuracy of estimating the efficiency of solar panels according to the total current of the solar panels of the SPS of spacecraft, mainly by ensuring the determination of the performance of each of the surfaces - both the front and the back - of each solar battery of the PSS. The invention can be used both on spacecraft and on other aircraft, as well as in ground conditions.

With regard to the conditions of operation in space, solar cells of the PSS are exposed to the factors of open space, which leads to their gradual degradation and the need to evaluate the current efficiency of solar cells, associated with obtaining the current values of their performance parameters.

The proposed technical solution provides the conditions for evaluating the performance of the front and rear surfaces of solar cells with two-sided photosensitivity based on the results of measuring the current generated by a complete set of photovoltaic cells of solar cells under a stable temperature regime and minimal effect on the generation of solar cell illumination current by a luminous flux other than solar - in relation to operating conditions in space - a light flux leaving the Earth.

The minimization of the influence on the generation of the solar panels illumination current by the light flux leaving the Earth is ensured by the fact that the measurements of the SB current are performed on the time interval in which the value of the solar battery current component generated by illuminating the solar panels with the light flux leaving the Earth does not exceed the measurement error solar battery current.

The use of measurements of the total SB current, made at the moments when the points of intersection of each of the planes in which the SB lie with the surface of the external environment, visible from the SB, are shaded from the Sun, makes it possible to determine the desired efficiency coefficients of the individual front and rear surfaces of the SB for due to the fact that at each considered moment of time, the SB current is generated due to the illumination of only one side of the SB - either only the front, or only the back.

The resulting technical result improves the accuracy of evaluating the efficiency of solar panels of the SEP SC in flight by obtaining accurate estimates of the efficiency (performance) of both the front and rear surfaces of individual solar panels that are part of the SEP with one current sensor, when it is provided to obtain TMI of the total current of all solar panels and there is no possibility of measuring and obtaining TMI current of individual solar cells.

The proposed technical solution makes it possible to provide the most identical conditions for measuring the current of solar batteries, according to which the efficiency of solar batteries of the SEP SC is evaluated, while the use of measurements of the current generated by a complete set of solar cells is implemented, which ensures maximum reliability of the data obtained on the performance of solar batteries.

The most identical conditions for measuring the current of solar batteries used to evaluate the efficiency of SEP SC batteries make it possible to increase the accuracy of their subsequent use, including the validity of comparing the obtained efficiency (performance) characteristics of solar batteries and the validity of judgments about their changes over time.

Knowledge of the current values of the efficiency (performance) parameters of both the front and rear surfaces of each individual solar battery of the SEP SC is necessary both for more accurate modeling of the functioning of the SEP SC in flight (in particular, for accurate prediction of the generation of solar batteries current when solving various problems of controlling the flight of a spacecraft, in including for optimal control of the angular position of the solar arrays of the spacecraft EPS), and for accurate analysis of the effects of the actual degradation of the solar arrays of the spacecraft (which is important both from the point of view of predicting the state and performance of these specific solar arrays for subsequent stages of the flight of this spacecraft, and from the point of view in terms of obtaining technical and technological data to improve the technology for the development of SEP spacecraft).

At present, everything is technically ready for the implementation of the proposed method. The industrial execution of the essential features characterizing the invention is not complicated and can be performed using existing technical means.

Claims (1)

A method for evaluating the efficiency of solar batteries of the power supply system of an apparatus, mainly spacecraft, including turning the solar panels to positions determined from the condition of minimizing the angle between the normal to the front surface of the solar battery and the direction to the Sun, measuring the total current of the solar panels and determining the current value of the luminous flux from the Sun and the angles of its incidence on the plane of the surface of the solar panels, characterized in that at one time interval the device is deployed, on which the solar panels are installed / placed, until the solar panels are fully illuminated by the Sun at angles between the direction to the Sun and the normals to the front surfaces of the solar panels are less than the specified acute angle, on another time interval, the indicated apparatus is deployed until the solar panels are fully illuminated by the Sun and the solar panels are rotated to a position at which the angles between the direction to the Sun and the normals to the rear surfaces of the sun than a given acute angle, on other 2n-2 time intervals, where n, n≥2 is the total number of solar panels, turn the indicated device until the solar panels are fully illuminated by the Sun and rotate less than n solar panels to a position at which the angles between the direction to the Sun and the normals to the back surfaces of the solar panels is less than the specified acute angle, provided that for each solar battery of the power supply system at least one time interval the front side of the solar battery is turned to the Sun and at least one time interval is turned to the Sun the back side of the solar battery, the measurement of the total current of the solar panels is performed at the described moments of their full illumination at time intervals when the points of intersection of each of the planes in which the solar panels lie with the surface of the external environment, visible from the solar panels, are shaded from the Sun, and determined component of the measured current from illuminated solar panels with a luminous flux other than solar does not exceed the current measurement error, and the efficiency of a separate solar battery is estimated by the current values generated by the solar battery when its front and back surfaces are illuminated, respectively, with solar radiation of the reference brightness along the normal to the surface of the solar battery, which determine according to measurements of the total current of solar cells, performed on the mentioned 2n time intervals during the indicated time intervals, taking into account the current value of the light flux from the Sun and the angles of its incidence on the plane of the surface of the solar cells.

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