RU2580593C2 - Method of discharging power from gyro of spacecraft with creating the magnetic moment - Google Patents

Abstract

FIELD: spacecraft.

SUBSTANCE: invention relates to controlling the angular movement of the spacecraft. For unloading the system of power gyroscopes from angular momentum current loops of a phased array (PAR) are used. According to the magnetic moments of these circuits the total value of the magnetic moment of the PAR in each mode of its operation is determined. Then the unloading point is calculated, generated by the interaction of the magnetic moments by PAR with Earth's magnetic field. When the condition of discharge is met determine the appropriate mode of operation PAR with the required discharge point and conduct discharge.

EFFECT: technical result of the invention is to improve the efficiency of discharge of power gyroscopes.

1 cl, 5 dwg

Description

The invention relates to space technology and can be used to unload a system of power gyroscopes (SG) spacecraft (SC) from the accumulated kinetic moment. In the orientation systems of modern spacecraft, they are widely used as executive organs of the SG (Raushenbakh B.V., Tokar E.N. Spacecraft orientation control. Moscow. "Science". 1974) [1]. They can significantly reduce the flow rate of the working fluid of the spacecraft jet engines during the flight program, however, they require constant or periodic unloading from the accumulated kinetic moment. One of the most effective methods of unloading is to use a control magnetic moment obtained from the interaction of the Earth's magnetic field with the magnetic moments inherent in the spacecraft itself.

There is a known method of unloading the spacecraft SG system, which consists in measuring the Earth's magnetic field induction (MPZ), measuring the accumulated kinetic moment in the SG system, determining the necessary projections of the magnetic moment of the system of magnetic actuating organs (IOI) for unloading the SG, forming a magnetic moment in the IOI, which interacting with MPZ, creates a control moment of forces that relieves the SG system (Kirilin A.N., Akhmetov R.N., Sollogub A.V., Makarov V.P. Methods for ensuring survivability of low-Earth orbit automatic sensing spacecraft and. Moscow. "Engineering". 2010) [2, p. 196]. The use of special MIO leads to additional consumption of electricity, and also reduces the mass of the payload brought to orbit.

A known method of forming the discharge torque for the exhaust gas system from the accumulated kinetic moment using current circuits of solar batteries (SB) (Patent RU 2030338 C1. MKI B64G 1/28 / Kovtun V.S., Kuzmichev A.Yu., Platonov V.N. The method of forming the discharge torque for the system of power gyroscopes of a spacecraft with solar batteries // Inventions. 1995. No. 7) [3]. The specified method of unloading the SG system as the closest in technical essence to the proposed invention is taken by the authors as a prototype. The essence of the method is to generate a control signal on the current circuits of the SB of the spacecraft to create magnetic moments, measure the vector of the kinetic moment accumulated in the system of power gyroscopes, measure the induction vector of the magnetic resonator, determine the unit vector of the discharge moment obtained from the interaction of the magnetic moments of the current circuits of the magnetic resonator with the magnetic determination of the conditions of SG discharge by the specified vector and vector of the accumulated kinetic moment, provision of the specified conditions by controlling the current circuits of the SB.

In the prototype method, there is no power consumption for the formation of the discharge torque, and it is also not required to have a special MIO on board the spacecraft. The main disadvantages of the prototype method include the impossibility of unloading the SG in the shadow intervals of the spacecraft orbit, as well as the need to develop a control system for the current circuits of the SB to be able to turn the circuits in the desired direction, providing unloading of the SG.

The objective of the invention is to increase the efficiency of SG unloading by increasing the value of the discharge torque obtained from the interaction of the magnetic moments of the current circuits formed in various spacecraft devices with a fault, as well as the use of the specified discharge torque in the shadow intervals of the spacecraft orbit.

в системе силовых гироскопов, измерение вектора индукции магнитного поля Земли $$\overrightarrow{B}$$

, определение, получаемого в результате взаимодействия магнитных моментов $$\overrightarrow{L}$$

токовых контуров с магнитным полем Земли, единичного вектора разгрузочного момента $$\overrightarrow{m}$$

To achieve the specified technical result in the method of unloading power gyroscopes of a spacecraft with a generated magnetic moment, including measuring the current value of the vector of the accumulated kinetic moment $$\overrightarrow{H}$$

in a system of power gyroscopes, measuring the vector of the magnetic field of the Earth $$\overrightarrow{B}$$

, determination resulting from the interaction of magnetic moments $$\overrightarrow{L}$$

current loops with the Earth's magnetic field, a unit vector of discharge torque $$\overrightarrow{m}$$

generating a control signal to the spacecraft current circuits by changing the magnitude and direction of the current flow to provide conditions for unloading power gyroscopes from the accumulated kinetic moment

,Where $$\overrightarrow{h}=\frac{\overrightarrow{H}}{\left|\overrightarrow{H}\right|}$$

,

обхода токовых контуров, определяют магнитные моменты для каждого токового контураpreliminary in qx diagram-forming circuits, where q = 1, 2, ..., Q, in each p-th mode of operation of the phased array, where p = 1, 2, ..., P, the currents in the power supply circuits I _pq and areas S are measured _pq contours, and also determine the direction of the normals $${\overrightarrow{n}}_{pq}$$

bypass current circuits, determine the magnetic moments for each current circuit

the magnetic moments for each current circuit determine the magnetic moment of the phased antenna array in each p-th mode of operation

разгрузочных моментов, создаваемых в результате взаимодействия магнитных моментов фазированной антенной решетки с магнитным полем Земли при $$\overrightarrow{L}={\overrightarrow{L}}_p$$

, далее при выполнении условия разгрузки силовых гироскопов от накопленного кинетического момента, где $$\overrightarrow{m}={\overrightarrow{m}}_p$$

, определяют $$\stackrel{⌢}{p}-e$$

режимы работы фазированной антенной решетки $$\stackrel{⌢}{p}\in P$$

для проведения разгрузки системы силовых гироскопов от накопленного кинетического момента, определяют значения проекции вектора разгрузочного момента на направление вектора $$\overrightarrow{h}$$

determine the values of unit vectors $${\overrightarrow{m}}_p$$

unloading moments created as a result of the interaction of the magnetic moments of the phased array antenna with the Earth’s magnetic field at $$\overrightarrow{L}={\overrightarrow{L}}_p$$

, then when the conditions for unloading power gyroscopes from the accumulated kinetic moment, where $$\overrightarrow{m}={\overrightarrow{m}}_p$$

determine $$\stackrel{⌢}{p}-e$$

Phased Array Modes $$\stackrel{⌢}{p}\in P$$

for unloading the system of power gyroscopes from the accumulated kinetic moment, determine the projection values of the vector of the unloading moment on the direction of the vector $$\overrightarrow{h}$$

, $${\overrightarrow{L}}_{\stackrel{⌢}{p}}$$

- значения векторов $${\overrightarrow{m}}_p$$

, $${\overrightarrow{L}}_p$$

для $$\stackrel{⌢}{p}-x$$

режимов работы фазированной антенной решетки, по максимальному значению $$\max \left({\pi }_{\overrightarrow{h}}{\overrightarrow{M}}_{\stackrel{⌢}{p}}\right)$$

определяют $$\stackrel{⌢}{p}\text{'}$$

-й режим работы фазированной антенной решетки для разгрузки системы силовых гироскопов и в случае выполнения условияWhere $${\overrightarrow{m}}_{\stackrel{⌢}{p}}$$

, $${\overrightarrow{L}}_{\stackrel{⌢}{p}}$$

- values of vectors $${\overrightarrow{m}}_p$$

, $${\overrightarrow{L}}_p$$

for $$\stackrel{⌢}{p}-x$$

operating modes of the phased array, at the maximum value $$\max \left({\pi }_{\overrightarrow{h}}{\overrightarrow{M}}_{\stackrel{⌢}{p}}\right)$$

determine $$\stackrel{⌢}{p}\text{'}\text{'}$$

-th operation mode of the phased array antenna for unloading the system of power gyroscopes and if the condition

- значение вектора $${\overrightarrow{m}}_{\overline{p}}$$

для $$\stackrel{⌢}{p}\text{'}$$

-го режима, производят повторное формирование разгрузочного момента путем изменения режима работы фазированной антенной решетки, формирование сигнала управления для разгрузки силовых гироскопов прекращают при получении значения $$\overrightarrow{H}=0$$

.Where $${\overrightarrow{m}}_{\stackrel{⌢}{p}\text{'}\text{'}}$$

is the value of the vector $${\overrightarrow{m}}_{\overline{p}}$$

for $$\stackrel{⌢}{p}\text{'}\text{'}$$

-th mode, re-forming the unloading moment by changing the operation mode of the phased antenna array, the formation of the control signal for unloading power gyroscopes is stopped when the value $$\overrightarrow{H}=0$$

.

The essence of the proposed method is the use of current loops of diagram-forming circuits (DOS) of the phased antenna arrays (PAR) of the spacecraft, which, when interacting with the magnetic field, create magnetic control moments to ensure the discharge of the SG from the accumulated kinetic moment.

To explain the proposed method, consider a headlamp consisting of modules (see Fig. 1), which are elements of a panel (see Fig. 2) of a transceiver active headlamp. The size of the modules is 480 × 480 × 40 in the central parts of the panel, along the edges - the size is 480 × 380 × 40. The panel contains µ ₁ = 22 modules of size 480 × 480 × 40 and µ ₂ = 16 modules of size 480 × 380 × 40. Each module contains an antenna sheet and elements of the formation of beams into signals with a nominal frequency band. The composition of the module in FIG. 1 includes:

- 64 antennas operating in a given frequency range, which are combined by an in-phase splitter-adder into 16 antenna elements;

- 16 transmit-receive switches;

- 16 receiving and 16 transmitting amplifiers;

- 16-channel microwave adder and splitter, in which controlled elements of the formation of beams are built-in;

- voltage converters + 50V (75V) to + 5V and other necessary voltages;

- digital control circuit.

The functional control circuit of the module contains 16 transmitting and receiving cells with a reversing amplifying path and controlled circular polarization of the radiation and signal reception. The basis of the design is a multilayer printed circuit board (MPP). One of the extreme layers is reserved for the wiring and installation of all attachments. Some of the layers in the MPP are layers of power and digital signals, including those transmitted to other MPPs within the headlamp panel. Between MPP, electrical signals and power are transmitted through flexible loops.

The architecture of the module corresponds to a bipolarization headlamp with crossed microstrip emitters. In this case, DOS of different polarizations are separated by a screen (Vendik OG, Parnes MD Antennas with electronic beam motion. Edited by L.D. Bahrakh. St. Petersburg, 2001) [4, p. 215]. Each DOS, when the headlight is operating, corresponds to a specific electric field. The field is characterized by a current circuit, covering a characteristic view of the area in the cross section of the DOS transmission line [4, p. 233]. In turn, the type of area depends on the type of dos. In this example, for DOS with serial power supply on a symmetrical strip line with directional couplers, the area of the current circuit looks like a rectangle [4, p. 233].

The magnitude of the current in the DOS circuit and the direction of its flow is determined by the operating modes of the PAR - “receive”, “transmit”, “receive-transmit”, changes in the signal power in the transmit-transmit path, which can be implemented in different frequency ranges with a turn of the current circuits in the reverse amplification path. Moreover, in antenna arrays with frequency scanning, the formation of different frequencies will correspond to different current DOS power circuits. Cases of electron-switched power supply, in which several beams are formed simultaneously, can serve as examples: these are the Butler matrix and the Luneberg lens [4, p. 208-209]. Power schemes in both cases involve changes in the formation of current circuits on the flat structural surface of the PAR. The final values of the current and the area of the circuit can also be affected by the technological features of the manufacture of the HEADLIGHTS, as well as the permissible deviations in the operation of electrical converters, through which the power supply of the DOS is provided.

Therefore, after the manufacture of the PAR, before the start of its operation, it is preliminarily measured in qx DOS, where q = 1, 2, ..., Q, in each p-th mode of operation of the phased array, where p = 1, 2, ..., P, the values of the currents in the power circuits I _pq and the areas S _{pq of the} circuits. To measure the area used thermographs (thermal imagers) - various kinds of infrared cameras that use wavelengths from medium infrared to terahertz range. As a result, images of electric (or thermal) fields are obtained for the used DOS types in different modes of their operation [4, p. 233], which measure the area of current circuits.

к каждому токовому контуру ДОС определяют исходя из логики работы переключателей антенной решетки по алгоритму коммутации схемы питания. По полученным данным определяют магнитные моменты $${\overrightarrow{L}}_{pq}$$

, см. (3).Normal directions $${\overrightarrow{n}}_{pq}$$

to each current circuit DOS is determined based on the logic of the operation of the switches of the antenna array according to the switching algorithm of the power circuit. According to the data determined magnetic moments $${\overrightarrow{L}}_{pq}$$

, see (3).

, n=1, 2,…,N, N⊂Q (фиг. 3, a), так и отрицательные $${\overrightarrow{L}}_{p1}^{-}\dots {\overrightarrow{L}}_{pm}^{-}$$

, m=1, 2,…,M, M⊂Q направления (фиг. 3, б). Модули указанных векторов могут также отличаться между собой. По определенным значениям собственных магнитных моментов для каждого модуля определяют магнитные моменты для панели ФАР (см. фиг. 2) в целом. Т.е. в результате определяют значение собственного магнитного момента панели фазированной антенной решетки в каждом p-м режиме ее работы по выражению (4), при этом значения q могут принимать как n-е, так и m-е значения. Следовательно, экспериментально-расчетным методом определяется собственный магнитный момент панели ФАР в каждом p-м режиме работы, где p=1, 2,…,Р. При этом в одних и тех же функциональных режимах («приема» или «передачи»), разными способами коммутации панелей, могут создаваться магнитные моменты разного знака. Таким образом, направлено, за счет реверсивного тракта питания отдельных модулей, обеспечивается формирование режимов работы панелей ФАР, в которых суммируются [см. (4)] только положительные $$\left({\overrightarrow{L}}_p:={\overrightarrow{L}}_{\sum }^{+}\right)$$

или отрицательные $${\overrightarrow{L}}_p:={\overrightarrow{L}}_{\sum }^{-}$$

магнитные моменты. В определенных режимах работы векторы разных знаков взаимно компенсируются, в таких случаях панель является «магнитоуравновешенной» $$({\overrightarrow{L}}_p=0)$$

. При отключении питания ФАР решетка также является «магнитоуравновешенной».As a result, for each PAR module it is possible to determine the magnitude and direction of these vectors (see Fig. 3). Moreover, these vectors can have as positive $${\overrightarrow{L}}_{p\mathrm{one}}^{+}...{\overrightarrow{L}}_{pn}^{+}$$

, n = 1, 2, ..., N, N⊂Q (Fig. 3a), and negative $${\overrightarrow{L}}_{p\mathrm{one}}^{-}...{\overrightarrow{L}}_{pm}^{-}$$

, m = 1, 2, ..., M, M⊂Q of the direction (Fig. 3, b). Modules of these vectors may also differ from each other. From certain values of the intrinsic magnetic moments for each module, the magnetic moments for the HEADLAMP panel are determined (see Fig. 2) as a whole. Those. as a result, the value of the intrinsic magnetic moment of the phased array antenna panel is determined in each pth mode of its operation by expression (4), while the q values can take both the nth and mth values. Therefore, by the experimental-calculation method, the intrinsic magnetic moment of the HEADLAMP panel is determined in each pth mode of operation, where p = 1, 2, ..., P. Moreover, in the same functional modes (“reception” or “transmission”), in different ways of switching panels, magnetic moments of different signs can be created. Thus, it is directed, due to the reversing power path of individual modules, that the operation modes of the HEADLIGHTER panels are formed, in which they are summarized [see (4)] only positive $$\left({\overrightarrow{L}}_p:={\overrightarrow{L}}_{\sum }^{+}\right)$$

or negative $${\overrightarrow{L}}_p:={\overrightarrow{L}}_{\sum }^{-}$$

magnetic moments. In certain operating modes, vectors of different signs are mutually compensated, in such cases the panel is “magnetically balanced” $$({\overrightarrow{L}}_p=0)$$

. When the power is switched off, the headlamp is also “magnetically balanced”.

If several such panels are installed on the spacecraft, then their total magnetic moment is determined by the previously specified expression (4). In this case, the magnetic moments of all current circuits of the DOS PHAR obtained in the compiled panels are summarized. In such cases, “magneto-equilibrium” as a whole can be achieved due to equal oppositely directed intrinsic magnetic moments of current loops in paired panels. And if one of the panels of the pair is used in operation, the corresponding component of the magnetic moment appears, which is inherent only to the working panel.

Thus, there are several ways to control the operating modes of the HEADLIGHTER for obtaining positive or negative intrinsic magnetic moments created by all current circuits of the DOS HEADLIGHTS or to obtain the conditions for their “magneto-balance”.

- магнитный управляющий момент от ФАР; $${\pi }_{\overrightarrow{h}}{\overrightarrow{M}}_L$$

- проекция вектора $${\overrightarrow{M}}_L$$

, на направление вектора $$\overrightarrow{h}=\frac{\overrightarrow{H}}{\left|\overrightarrow{H}\right|}$$

, остальные обозначения соответствуют ранее введенным.In FIG. 4 is a diagram of the SG discharge from the accumulated kinetic moment using the PAR. In this case, the following notation is introduced: 1 - KA; 2 - headlight panel; OXYZ is the associated basis of the spacecraft, whose axes coincide with the main central axes of inertia; $${\overrightarrow{M}}_L$$

- magnetic control torque from the headlamp; $${\pi }_{\overrightarrow{h}}{\overrightarrow{M}}_L$$

- vector projection $${\overrightarrow{M}}_L$$

to the direction of the vector $$\overrightarrow{h}=\frac{\overrightarrow{H}}{\left|\overrightarrow{H}\right|}$$

, the remaining notation corresponds to the previously entered.

обеспечивает разгрузку СГ от накопленного кинетического момента, так как за счет тупого угла между векторами $${\overrightarrow{M}}_L$$

и $$\overrightarrow{H}$$

выполняется условие (2) для $${\overrightarrow{m}}_p=\overrightarrow{m}$$

, $$\overrightarrow{L}={\overrightarrow{L}}_p={\overrightarrow{L}}_{\sum }^{+}$$

. При этом $${\overrightarrow{m}}_p=\frac{{\overrightarrow{L}}_{\sum }^{+}}{\left|{\overrightarrow{L}}_{\sum }^{+}\right|}\times \frac{\overrightarrow{B}}{\left|\overrightarrow{B}\right|}$$

.The control moment indicated on the diagram $${\overrightarrow{M}}_L={\overrightarrow{L}}_{\sum }^{+}\times \overrightarrow{B}$$

provides SG unloading from the accumulated kinetic moment, since due to an obtuse angle between vectors $${\overrightarrow{M}}_L$$

and $$\overrightarrow{H}$$

condition (2) is satisfied for $${\overrightarrow{m}}_p=\overrightarrow{m}$$

, $$\overrightarrow{L}={\overrightarrow{L}}_p={\overrightarrow{L}}_{\sum }^{+}$$

. Wherein $${\overrightarrow{m}}_p=\frac{{\overrightarrow{L}}_{\sum }^{+}}{\left|{\overrightarrow{L}}_{\sum }^{+}\right|}\times \frac{\overrightarrow{B}}{\left|\overrightarrow{B}\right|}$$

.

, соответствующий одному из возможных режимов работы ФАР, может иметь и другие значения при выполнении условия (2) в p-x режимах работы ФАР. Следовательно, необходимо оценить каждый из возможных вариантов разгрузки СГ, для последующего выбора наиболее эффективного режима работы ФАР с точки зрения достижения поставленной цели разгрузки СГ, при сохранении основного функционального предназначения решетки.The considered example is a special case of SG unloading, since the vector $${\overrightarrow{L}}_p$$

corresponding to one of the possible operation modes of the HEADLIGHTER can have other values when condition (2) is fulfilled in the px HEADLIGHT operation modes. Therefore, it is necessary to evaluate each of the possible options for unloading the SG, for the subsequent selection of the most effective mode of operation of the HEADLIGHTS from the point of view of achieving the goal of unloading the SG, while maintaining the main functional purpose of the grill.

режимы работы ФАР из конечного множества Р возможных режимов ее работы, при которых будет производиться разгрузка системы СГ от накопленного кинетического момента $$\left(\stackrel{⌢}{p}\in P\right)$$

исходя из выполнения условия (2). При этом определяют значение магнитного момента $${\overrightarrow{L}}_{\widehat{p}}$$

ФАР в каждом $$\stackrel{⌢}{p}-м$$

режиме ее работы, а также значение $${\overrightarrow{m}}_{\widehat{p}}$$

при $$L_p={\overrightarrow{L}}_{\widehat{p}}$$

. Далее по каждому вектору $${\overrightarrow{M}}_{\widehat{p}}={\overrightarrow{L}}_{\widehat{p}}\times \overrightarrow{B}$$

определяют его проекцию на направление вектора $$\overrightarrow{h}$$

по выражению (5). Из полученного множества $$\mu \left({\pi }_{\overrightarrow{h}}{\overrightarrow{M}}_{\widehat{p}}\right)$$

, $$\widehat{p}=\widehat{1},\widehat{2},\dots ,$$

$$\widehat{p}\in P$$

, определяют максимальное значение $$\max \left({\pi }_{\overrightarrow{h}}{\overrightarrow{M}}_{\widehat{p}}\right)$$

, по которому, в свою очередь, выбирают $$\stackrel{⌢}{p}\text{'}$$

-й режим работы ФАР для разгрузки системы СГ от накопленного кинетического момента. Выбранное наибольшее из возможных значений проекций разгрузочного момента на направление вектора накопленного кинетического момента в системе СГ позволяет минимизировать продолжительность разгрузки и тем самым максимально эффективным образом достичь ее цели.To do this, determine $$\stackrel{⌢}{p}-e$$

PAR operating modes from a finite set P of possible modes of its operation, in which the SG system will be unloaded from the accumulated kinetic moment $$\left(\stackrel{⌢}{p}\in P\right)$$

based on the fulfillment of condition (2). In this case, determine the value of the magnetic moment $${\overrightarrow{L}}_{\widehat{p}}$$

Headlamp in each $$\stackrel{⌢}{p}-m$$

mode of operation, as well as the value $${\overrightarrow{m}}_{\widehat{p}}$$

at $$L_p={\overrightarrow{L}}_{\widehat{p}}$$

. Next for each vector $${\overrightarrow{M}}_{\widehat{p}}={\overrightarrow{L}}_{\widehat{p}}\times \overrightarrow{B}$$

determine its projection on the direction of the vector $$\overrightarrow{h}$$

by expression (5). From the resulting set $$\mu \left({\pi }_{\overrightarrow{h}}{\overrightarrow{M}}_{\widehat{p}}\right)$$

, $$\widehat{p}=\widehat{\mathrm{one}},\widehat{2},...,$$

$$\widehat{p}\in P$$

determine the maximum value $$\max \left({\pi }_{\overrightarrow{h}}{\overrightarrow{M}}_{\widehat{p}}\right)$$

which, in turn, is chosen $$\stackrel{⌢}{p}\text{'}\text{'}$$

-th mode of operation of the headlamp for unloading the SG system from the accumulated kinetic moment. The selected largest of the possible values of the projections of the unloading moment on the direction of the vector of the accumulated kinetic moment in the SG system allows one to minimize the duration of unloading and thereby achieve its goal in the most efficient way.

, а также выполнение условия (6) отсутствия разгрузки с учетом использования управляющего магнитного момента с единичным вектором $${\overrightarrow{m}}_{\stackrel{⌢}{p}\text{'}}$$

, свойственного для $$\stackrel{⌢}{p}\text{'}$$

-го режима работы ФАР.In the process of SG discharge, the presence of the accumulated kinetic moment, i.e. $$\overrightarrow{H}\ne 0$$

, as well as the fulfillment of condition (6) of the absence of unloading, taking into account the use of a control magnetic moment with a unit vector $${\overrightarrow{m}}_{\stackrel{⌢}{p}\text{'}\text{'}}$$

characteristic of $$\stackrel{⌢}{p}\text{'}\text{'}$$

FAR operation mode.

и $$\overrightarrow{H}$$

становится прямым (см. фиг. 4). А в случае острого угла система СГ будет дополнительно нагружаться кинетическим моментом от действия на КА рассмотренного управляющего момента.As follows from (6), unloading is impossible in the case when the angle between the vectors $${\overrightarrow{M}}_L$$

and $$\overrightarrow{H}$$

becomes direct (see Fig. 4). And in the case of an acute angle, the SG system will be additionally loaded with a kinetic moment from the action of the considered control moment on the spacecraft.

If the specified condition (6) is fulfilled, to ensure further unloading, re-formation of the unloading moment is performed in the above manner. Moreover, the values of the magnetic moment of the phased array is determined by the expression (4) for each p-th mode of its operation at the time the condition (6) is satisfied.

). Формирование сигнала управления для разгрузки силовых гироскопов прекращают выбором одного из «магнитоуравновешенных» режимов работы ФАР, при котором L_p=0.Then continue to unload the SG until it is completed (to obtain the value $$\overrightarrow{H}=0$$

) The formation of a control signal for unloading power gyroscopes is stopped by selecting one of the “magnetically balanced” modes of operation of the PAR, at which L _p = 0.

Implementation of the proposed method is carried out on the basis of the spacecraft onboard control complex (BCC), the necessary composition of which is presented in FIG. 5. BKU is a centrally distributed structure of airborne systems:

1 - on-board digital computer system (BTsVS);

2 - traffic control and navigation system (SUDN);

3 - on-board equipment control system (SUBA);

4 - on-board control equipment (BAU) PAR;

5 - on-board measurement system (SBI);

6 - on-board equipment of the service control channel (BA SKU).

In this case, the first output of the BCVS 1 is connected to the input of the VACS 2, the output of which is connected to the first input of the BCVS 1. The second output of the BCVS 1 is connected to the input of SUBA 3, the output of which is connected to the input of the BAU FAR 4. The three outputs of the BAU FAR 4 are connected (multichannel) with three inputs of SBI 5. The fourth input of SBI 5 is connected to the third output of the BCVS 1. And the output of SBI 5 is connected to the second input of the BCVS 1. The fourth output of the BCVS 1 is connected to the input of the BCU 6. And the output of the specified on-board equipment is connected to the third input of the BCVS 1.

In addition to the indicated symbols in FIG. 5, an additional ground control complex (GCC) of the spacecraft (pos. 7) is shown, which interacts with BA SKU 6, directions for transmitting telemetric (TM) and command-program information (KPI), as well as operational control information (IOC). The integration of the above systems and on-board equipment into a single control complex is carried out using the software of the BKU located in digital computers and interface devices of the BCVS.

To implement the proposed method, BKU software provides a solution to the following tasks (see Fig. 5):

- Calculation and control of the orientation of the spacecraft (pos. 1, 2);

- management and control of the inclusion of on-board systems (pos. 1-6);

- reception, storage, processing and distribution of KPI received from GCC (item 7).

в СГ. Далее алгоритмами БЦВС производится выбор режима работы ФАР, обеспечивающего разгрузку СГ от накопленного кинетического момента в соответствии с ранее описанной логикой формирования разгрузочного момента. Команда на выбор режима работы ФАР транслируется через СУБА 3 в БАУ ФАР 4. СУБА 3 осуществляет коммутацию и распределение электроэнергии потребителям, в том числе для БАУ ФАР 4. Кроме того, СУБА 3 осуществляет прием командной информации от БЦВС, производит ее преобразование, усиление и распределение по другим системам и бортовой аппаратуре КА. БА ФАР 4, в свою очередь, производит преобразование, усиление и распределение команд управления отдельными модулями ФАР.With the help of the BCVS 1 algorithms that ensure the operation of the kinematic and dynamic circuits of the SUDN 2 [1], the given orientation is constructed and maintained. Moreover, SG [1] are used as executive bodies, from each of which the measured values of the kinetic moment are transmitted to the BCVS. From the indicated measured values, the value of the vector of the accumulated kinetic moment is determined $$\overrightarrow{H}$$

in SG. Further, the BCVS algorithms make the choice of the operation mode of the HEADLIGHTER, which ensures the unloading of the SG from the accumulated kinetic moment in accordance with the previously described logic of the formation of the unloading moment. The command to select the operation mode of the HEADLIGHTS is transmitted through SMSA 3 to the BAU HEADLIGHT 4. SUBA 3 carries out switching and distribution of electricity to consumers, including the BAU HEADLAMP 4. In addition, SMSA 3 receives command information from the BCVS, converts, amplifies and distribution to other spacecraft systems and equipment. BA FAR 4, in turn, converts, amplifies and distributes control commands for individual PAR modules.

About the current state of the HEADLIGHTS information from current sensors installed in the voltage converters of the modules comes in the form of TM information through SBI 5 to the BCVS 1. At the same time, the connection of the BAU PHAR 4 measuring channels to SBI 5 or re-confirmation in the form of control commands for their use is made from BTsVS 1 simultaneously with the issuance of a command in SMSA 3. By the same command, an array of digital PKI is formed for transmission through BA SKU 6 to the receiving means of NKU 7 about the choice of the headlight operation mode. In NKU 7, the operation of the selected HEADLIGHT modes is monitored both by the IOC from the spacecraft and by the characteristics of the radio signal when it is directly received and transmitted in a satellite communication system of a certain range provided by the active headlight.

According to the results of monitoring the operation of the HEADLIGHTS, as well as the work of the SG, if necessary, the control commands from the NKU 7 through the BA of the SKU 6 with the formation of the KPI entering the BCVS 1, the control modes of the HEADLIGHT can be forced to change.

Let us estimate the magnitude of the control moment created by the own magnetic moments of the headlamps of the design described above. In accordance with (3), we determine for a single DOS of the PAR module shown in FIG. 1, the value of the intrinsic magnetic moment in the rth mode of operation

For the first module with the number of DOS z ₁ = 64 and the second module with the number of DOS z ₂ = 48, the values of the intrinsic magnetic moments will be respectively equal

For one PAR panel (r = 1) containing the number of modules µ ₁ = 22 and µ ₂ = 16, in accordance with (4), the intrinsic magnetic moment is

Promising spacecraft can contain up to 14 of these panels (r = 14). Then the maximum intrinsic magnetic moment of the entire PAR, with vector unidirectionality of the DOS moments, will be equal to

. При этом в штатной ориентации КА векторы $$\overrightarrow{L}$$

и $$\overrightarrow{B}$$

взаимно перпендикулярны. Тогда управляющий момент М_L будет равенNext, we will evaluate the control moment for a spacecraft containing a phased array and located in a geostationary orbit, where $$\left|\overrightarrow{B}\right|\approx 0.5\times {10}^{-\mathrm{four}}T$$

. Moreover, in the standard orientation of the spacecraft, the vectors $$\overrightarrow{L}$$

and $$\overrightarrow{B}$$

mutually perpendicular. Then the control moment M _L will be equal to

Comparative estimates showed that the obtained magnetic control moment is more than an order of magnitude when compared with the gravitational moment and the moment from the light pressure force acting on the same spacecraft. Since it is difficult to control the indicated moments with the regular orientation of the spacecraft, by forming the controlling magnetic moment by the proposed method, it is possible to counter the effect of other moments on the spacecraft, thereby reducing the load on the SG system by the kinetic moment. Ultimately, this leads to savings in the working fluid of jet engines used for unloading SG from the accumulated kinetic moment [1].

Bibliography

1. Raushenbakh B.V., Tokar E.N. Spacecraft orientation control. Moscow. "The science". 1974.

2. Kirilin A.N., Akhmetov R.N., Sollogub A.V., Makarov V.P. Methods for ensuring survivability of low-orbit automatic spacecraft sensing the Earth. Moscow. "Engineering". 2010.

3. Patent RU 2030338 C1. MKI B64G 1/28 / Kovtun V.S., Kuzmichev A.Yu., Platonov V.N. The method of forming the discharge torque for the system of power gyroscopes of a spacecraft with solar batteries // Inventions. 1995. No. 7.

4. Vendik O.G., Parnes M.D. Antennas with electronic beam movement. Edited by L.D. Bahraha. St. Petersburg, 2001.

Claims (1)

A method of unloading power gyroscopes of a spacecraft with a generated magnetic moment, including measuring the current value of the accumulated kinetic moment vector $$\overrightarrow{H}$$

 in a system of power gyroscopes, measuring the vector of the magnetic field of the Earth $$\overrightarrow{B}$$

, determination of the resulting magnetic moment interaction $$\overrightarrow{L}$$

 current circuits of a spacecraft with a magnetic field of the Earth of a unit vector of unloading moment $$\overrightarrow{m}$$

generating a control signal to the current circuits of the spacecraft by changing the magnitude and direction of the current flow to provide conditions for unloading power gyroscopes from the accumulated kinetic moment

Where $$\overrightarrow{h}=\frac{\overrightarrow{H}}{\left|\overrightarrow{H}\right|}$$

,
characterized in that previously inqdiagramming schemes, whereq = 1, 2, ... Qin eachp-m mode of operation of the phased antenna array, wherep = 1, 2, ... Pmeasure current values in power circuitsI _pq and areasS _pq contours, and also determine the direction of the normals $${\overrightarrow{n}}_{pq}$$

 bypass current circuits, determine the magnetic moments for each current circuit

the magnetic moments for each current circuit determine the value of the magnetic moment of the phased antenna array in eachR-m mode of operation

determine the values of unit vectors $${\overrightarrow{m}}_p$$

 unloading moments created as a result of the interaction of the magnetic moments of the phased array antenna with the Earth’s magnetic field at $$\overrightarrow{L}={\overrightarrow{L}}_p$$

, then when the conditions for unloading power gyroscopes from the accumulated kinetic moment, where $$\overrightarrow{m}={\overrightarrow{m}}_p$$

determine $$\stackrel{⌢}{p}-e$$

 Phased Array Modes $$\stackrel{⌢}{p}\in P$$

 for unloading the system of power gyroscopes from the accumulated kinetic moment, determine the projection values of the unloading moment vector on the direction of the vector $$\overrightarrow{h}$$

Where $${\overrightarrow{m}}_{\stackrel{⌢}{p}}$$

, $${\overrightarrow{L}}_{\stackrel{⌢}{p}}$$

 - values of vectors $${\overrightarrow{m}}_p$$

, $${\overrightarrow{L}}_p$$

 for $$\stackrel{⌢}{p}-x$$

 operating modes of the phased array, at the maximum value $$\max \left({\pi }_{\overrightarrow{h}}{\overrightarrow{M}}_{\stackrel{⌢}{p}}\right)$$

 determine $$\stackrel{⌢}{p}\text{'}\text{'}$$

-th operation mode of the phased array antenna for unloading the system of power gyroscopes and if the condition

Where $${\overrightarrow{m}}_{\stackrel{⌢}{p}\text{'}\text{'}}$$

 is the value of the vector $${\overrightarrow{m}}_{\stackrel{⌢}{p}}$$

 for $$\stackrel{⌢}{p}\text{'}\text{'}$$

-th mode, re-forming the discharge moment by changing the operating mode of the phased antenna array, and the formation of the control signal for unloading power gyroscopes is stopped when the value $$\overrightarrow{H}=0$$

.

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