RU2536765C2 - Method of controlling orbiting spacecraft - Google Patents

Abstract

FIELD: physics; control.

SUBSTANCE: invention relates to controlling movement of a spacecraft fitted with a heat radiator and a solar panel. The method includes flying the spacecraft on an orbit around a planet and turning the solar panel in a position corresponding to the alignment of the normal to the working surface of the solar panel with the direction towards the Sun; performing orbital orientation of the spacecraft, where the plane of rotation of the solar panel is parallel to the plane of the orbit of the spacecraft and the solar panel is located relative to the plane of the orbit on the side of the Sun; determining the maximum value of the angle between the velocity vector of the spacecraft and the perpendicular to the transverse axis of rotation of the solar panel, passing through the surface of the radiator; determining the orbital altitude of the spacecraft and the angle between the direction towards the Sun and the plane of the orbit of the spacecraft; based on the orbital altitude and the angle, determining the orbit passes where the duration of the illuminated part of the pass exceeds the difference between the orbiting period of the spacecraft and the required duration of the heat release by the radiator on the pass; on the said orbit passes, when the spacecraft passes through the illuminated part of the pass, the solar panel is turned around the transverse axis of rotation until the intersection of the line passing through the region of the surface of the radiator facing the Sun and directed towards the Sun with the solar panel; turning the solar panel around the longitudinal axis of rotation until the angle between the normal to the working surface of the solar panel and the direction towards the Sun assumes a minimum value. The said solar panel rotations are performed within a calculated time interval.

EFFECT: high efficiency of the radiator by creating conditions for natural cooling thereof during eclipse of the solar panel for any altitude of an almost circular orbit of the spacecraft.

5 dwg

Description

The invention relates to the field of space technology and can be used in controlling the movement of spacecraft (SC).

The spacecraft are equipped with solar panels (SB), which generate electricity to ensure the functioning of the spacecraft. During the flight operations of the spacecraft, on-board equipment is involved, the elements of which are heated during operation. The generated heat is used to control the spacecraft, and its excess is discharged into the space surrounding the spacecraft through radiators, heat emitters. In this case, heat discharge is most effective in shadow areas of the near-Earth orbit, during which the entire surface of the radiator-heat emitter is not illuminated by direct solar radiation, and less effective in areas of the orbit illuminated by the Sun, when heat release occurs mainly from those parts of the heat-radiator, which are obscured by the design elements of the spacecraft (Favorsky ON, Kadaner YS. Issues of heat transfer in space. M: Higher school, 1972).

A known method of controlling an orbital spacecraft (AS Eliseev Space Flight Engineering. M .: Mashinostroenie, 1983), which includes turning the SB into its working position on the Sun and performing an orbital flight of the spacecraft around the planet, in which heat is released by the radiator-heat emitter at the time it is located The spacecraft in the shadow of the planet, as well as at the moments of the light part of the revolution, in which, with the current orientation of the spacecraft, the spacecraft design obscures the radiator-radiator from direct sunlight. In this method, heat is released by the radiator-heat emitter due to the natural cooling of the radiator-heat emitter at the time of its shadowing by the planet or spacecraft designs. The disadvantage of this method is that it, in the General case, does not guarantee the presence on the light part of the orbit of the shading of the radiator-radiator by the design of the spacecraft. For example, when the spacecraft is in the “solar” orbit (when there is no shadow on the orbit), the absence of shadowing of the heat sink radiator by the spacecraft design means that the heat sink and heat sink are not shadowed throughout the turn, which significantly reduces the efficiency of the radiator-heat sink performing its functions.

A known method of controlling the orbital spacecraft (Malozemov V.V. Thermal conditions of spacecraft. M .: Mashinostroenie, 1980), adopted as a prototype, which includes the orbital flight of the spacecraft around the planet, the rotation of the satellites in the working position on the sun and the rotation of the spacecraft before the radiator is shaded -heater design of the spacecraft. In this method, it is guaranteed that heat is removed by the radiator-heat emitter due to the natural cooling of the radiator-heat emitter at the time of its shadowing by the spacecraft structure.

The prototype method has a significant drawback - to create conditions for the natural cooling of the radiator-heat radiator due to the shading of the spacecraft design by this method, it is necessary to continuously perform the aforementioned special rotation of the spacecraft, which, on the one hand, requires additional energy costs for its implementation, and on the other hand parties, the implementation of the aforementioned special rotation of the spacecraft in the general case may contradict the construction of the required target orientation of the spacecraft — the orientation in which the spacecraft should be to solve his targets. Thus, in the process of solving the target tasks of the spacecraft, which is accompanied by the construction of the required target orientation of the spacecraft, in the general case, conditions are not created for the natural cooling of the radiator-radiator due to its shadowing, which affects the efficiency of the functioning of the radiator-radiator.

The problem to which the present invention is directed, is to increase the efficiency of the radiator-heat radiator mounted on a spacecraft equipped with mobile SB.

The technical result achieved by the implementation of the present invention is to create additional conditions for the natural cooling of the heat sink-radiator by shading it with mobile SB SCs.

The technical result is achieved by the fact that in the control method of the orbital spacecraft, which includes performing an orbital flight of the spacecraft with a radiator-heat radiator placed on it in an orbit around the planet and turning the SB installed with two degrees of freedom on the spacecraft into the working position corresponding to the normal to the working surface SB with a direction to the Sun, additionally, the spacecraft’s orbital orientation is built, in which the plane of rotation of the SB is parallel to the plane of the orbit of the SC and SB located relative to the plane about orbits from the side of the Sun, determine the maximum value of the angle between the spacecraft velocity vector and the perpendicular to the transverse axis of rotation of the SB passing through the surface of the heat sink, determine the angle between the direction to the sun and the spacecraft’s orbit, determine the height of the spacecraft’s orbit, according to a certain orbit height and a certain the value of the angle between the direction to the Sun and the orbital plane of the spacecraft determines the orbits of the orbit, on which the duration of the illuminated part of the revolution exceeds the difference between the period of revolution of the spacecraft and the required duration In terms of the time of heat loss by the radiator-radiator on the orbit and on the above-mentioned orbit, when the spacecraft passes through the illuminated part of the orbit, the SB is rotated around the transverse axis of rotation of the SB until the straight line passes through the surface of the radiator-heat radiator facing the Sun and directed to the Sun with the SB and rotation of the SB around the longitudinal axis of rotation of the SB until the angle between the normal to the working surface of the SB and the direction to the Sun reaches the minimum value, while the above-described turns of the SB are performed during of total duration k · T P within a time interval, start and end points which are calculated respectively by the formulas:

$$t_{\mathrm{one}}=t_S+\frac{\mathrm{<figure-callout\; id="2"\; label="P"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">P</figure-callout>}}{2\cdot \pi }(\eta -\gamma ),{\mathrm{<figure-callout\; id="2"\; label="t"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">t</figure-callout>}}_2=t_S+\frac{\mathrm{<figure-callout\; id="2"\; label="P"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">P</figure-callout>}}{2\cdot \pi }(\eta +\pi +\gamma ),$$

Where $$\gamma =\arcsin \frac{L^2-D^2-{\mathrm{<figure-callout\; id="2"\; label="E"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">E</figure-callout>}}^2\cdot \mathrm{<figure-callout\; id="2"\; label="c\; t\; g"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">c\; </figure-callout>}t{g}^{}{}^2\mathrm{<figure-callout\; id="2"\; label="\beta "\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">\beta </figure-callout>}}{2\cdot D\cdot E\cdot ctg\beta },$$

k is a coefficient characterizing the required length of time for heat release by the heat sink-radiator at each turn and equal to the ratio of the necessary duration of time for heat release on the turn to the duration of the turn,

P is the spacecraft circulation period,

T is the duration of the shadow part of the coil,

t _s is the instant of passage of the spacecraft of the sunflower point of the revolution,

η is the maximum value of the angle between the spacecraft velocity vector and the perpendicular to the transverse axis of rotation of the SB passing through the surface of the heat sink, the positive direction of the angle reference is from the velocity vector towards the spacecraft radius vector,

L is the length of the SB along the longitudinal axis of its rotation,

D is the distance from the transverse axis of rotation of the SB to the farthest point from the axis of the surface of the radiator-radiator,

E is the distance from the plane of rotation of the SB to the farthest point from the plane of the surface of the radiator-radiator,

β is the angle between the direction to the Sun and the orbital plane of the spacecraft.

The essence of the invention is illustrated in figure 1 ÷ 5, which presents: figure 1 - diagram of the relative position of the SB and the radiator-heat emitter relative to the direction to the Sun, illustrating a view in the plane of the orbit, figure 2, 3, 4 - diagram of the mutual the position of the SB and the radiator-radiator relative to the direction to the Sun, illustrating the end view of the orbit plane, Fig. 5 is a diagram explaining the determination of the angle between the direction to the Sun and the spacecraft orbit plane, at which the duration of the shadow part of the orbit is equal to the required length the duration of heat release by the radiator-radiator on the coil.

Figure 1 ÷ 5 introduced the notation:

1 - spacecraft orbit;

2 - the longitudinal axis of rotation of the SB;

3 - the transverse axis of rotation of the SB;

4 - radiator-heat radiator;

5 - perpendicular to the transverse axis of rotation of the SB passing through the surface region of the radiator-heat emitter facing the Sun,

6 - plane of rotation of the SB;

S is the direction vector to the Sun;

S _p is the projection of the direction to the Sun on the orbit plane;

O is the center of the planet;

β is the angle between the direction to the Sun and the orbital plane of the spacecraft;

A _s - the position of the spacecraft in the sunflower point of the revolution;

And ₁ , And ₂ - the position of the spacecraft at moments t ₁ , t ₂ ;

AC, A ₁ C ₁ , A ₂ C ₂ , A ₃ C ₃ - the distance from the transverse axis of rotation of the SB to the farthest point from the axis of the surface of the radiator-heat emitter facing the Sun;

AB, A ₁ B ₁ , A ₂ B ₂ , A ₃ B ₃ .- the distance from the plane of rotation of the SB to the point farthest from the plane of the plane facing the Sun on the surface area of the radiator-heat radiator;

VM, B ₁ M ₁ , B ₂ M ₂ , B ₃ M ₃ - a segment of the longitudinal axis of rotation of the SB, concluded between the beginning and end of the SB;

F ₁ , F ₂ - the position of the SC at the beginning and end of the shadow portion of the coil;

F _s - the position of the spacecraft at the time of the middle of the shadow portion of the coil;

Z is the surface of the planet.

Let us explain the proposed method of action.

We assume that the SB satellites are installed with two degrees of freedom: the SB panel rotates around the longitudinal axis of rotation of the SB and around the transverse axis of rotation of the SB. Moreover, the rotation of the SB around the transverse axis of rotation of the SB consists in turning the longitudinal axis of rotation of the SB around the transverse axis of rotation of the SB. In this case, we consider a control system for the position of the SB, in which the transverse axis of rotation of the SB directly passes through the beginning of the longitudinal axis of rotation of the SB and is perpendicular to it.

We assume that the SBs are made “opaque”: SBs delay the flow of solar energy coming into them and can obscure the outer surface of the spacecraft from the Sun.

We assume that the SB have an elongated rectangular shape, and the length of the SB is measured along the longitudinal axis of rotation of the SB. The width of the SB is not less than the linear size of the surface of the radiator-heat emitter.

In the proposed method, an orbital flight of a spacecraft is carried out with a radiator-heat emitter placed on it around the planet in a circumcircular orbit.

Perform a turn of the SB into the working position, corresponding to the combination of the normal to the working surface of the SB with the direction to the Sun. In this orientation, the SB provides the maximum supply of electricity.

The construction of the orbital orientation of the spacecraft is performed, in which the plane of rotation of the SB is parallel to the plane of the orbit of the spacecraft and is located relative to the plane of the orbit on the side of the sun. This corresponds to the fact that the transverse axis of rotation of the SB is perpendicular to the plane of the orbit of the spacecraft and the SB is located relative to the plane of the orbit from the side of the Sun.

After constructing the orbital orientation, it is maintained and the maximum value of the angle η between the spacecraft velocity vector and the perpendicular to the transverse axis of rotation of the SB passing through the surface of the radiator-heat emitter is determined, the positive direction of the reference angle η is from the velocity vector in the direction of the spacecraft radius vector.

The angle between the direction to the Sun and the orbit plane of the spacecraft β is determined (we assume that always β≥0).

Determine the height of the orbit of the spacecraft N.

Using certain values of the angle between the direction to the Sun and the orbit plane of the spacecraft β and the height of the orbit of the spacecraft N, the orbits of the orbit are determined (selected) at which the duration of the illuminated part of the revolution exceeds the difference between the spacecraft’s revolution period and the required duration of the heat release time by the radiator-heat radiator on the orbit (data turns there is no way to provide the required duration of natural cooling of the heat sink in the shadow of the planet).

The definition (selection) of such turns is carried out, for example, as follows.

At the current altitude of the orbit of the spacecraft in the altitude range [H ₁ , H ₂ ]:

$$H_{\mathrm{one}}\le H\le {\mathrm{<figure-callout\; id="2"\; label="H"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">H</figure-callout>}}_2,\text{(one)}$$

$$H_{\mathrm{one}}=\frac{R}{\sin \left(\arccos \left(\cos (k\cdot \pi )\cdot \cos {\beta }_{\max }\right)\right)}-R,\text{(2)}$$

$$\begin{array}{l}{\mathrm{<figure-callout\; id="2"\; label="H"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">H</figure-callout>}}_2=\frac{R}{\sin (k\cdot \pi )}-R,\text{(3)}\\ \end{array}$$

$$\beta \max =\min \left\{|\; |\; |i|\; |\; |+\epsilon ,\frac{\pi }{2}\right\},\text{(four)}$$

where k is a coefficient characterizing the necessary length of time for heat dissipation by the radiator-heat emitter at each turn and equal to the ratio of the necessary duration of time for heat rejection on the turn to the duration of the turn,

R is the radius of the planet,

β _max ^{_ the} maximum value that can take the angle between the direction to the Sun and the orbital plane of the spacecraft,

i is the inclination angle of the SC orbit,

ε is the inclination angle of the ecliptic (ε ~ 23 ° 26 '),

we select only those turns at which the current value of the angle between the direction to the Sun and the orbit plane β is greater than the value β *, at which the duration of the shadow part of the orbit is equal to the required duration of the heat release time by the heat-radiator on the orbit:

$$\beta >\beta *,\left(\text{5}\right)$$

$$\beta *=\arccos \frac{\cos \theta }{\cos \lambda },\text{(6)}$$

$$\sin \theta =\frac{R}{R+H}.\text{(7)}$$

$$\lambda =\frac{\mathrm{<figure-callout\; id="2"\; label="T"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">T</figure-callout>}}{2}\cdot \frac{2\cdot \pi }{P},\text{(8)}$$

$$T=k\cdot P,\text{(10)}$$

where θ is the angular half-solution of the planet’s disk visible from the spacecraft,

λ is the angular half-solution of the shadow part of the orbit, measured from the center of the planet,

P is the spacecraft circulation period,

T is the duration of the shadow part of the coil.

Condition (5) corresponds to the fact that the duration of the shadow part of these orbit orbits is less than the required duration of the time of heat release by the radiator-heat emitter on the orbit. Under condition (5), the shadow on the coil is either completely absent, or its duration is shorter than the required duration of the heat release time by the radiator-heat emitter on the coil. If condition (5) is not fulfilled (for (β≤β *), then on this coil the duration of the shadow part of the coil is greater than or equal to the required duration of the heat release time by the heat sink-radiator on the coil.

At the current altitude of the orbit of the spacecraft is greater than the height of H ₂ :

$${\mathrm{<figure-callout\; id="2"\; label="H"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">H</figure-callout>}}_2<H,\text{(10)}$$

we select all the turns, because when (10) is fulfilled, the shadow on all turns is either absent, or its duration is shorter than the required duration of the time of heat release by the radiator-heat emitter on the turn.

At the current altitude of the spacecraft’s orbit, it is less than the height H ₁ (for H <H ₁ ), there is a shadow part on any turn and its duration is always longer than the required duration of the heat release time by the heat sink-radiator on the turn.

On selected orbits, when passing through the spacecraft of the illuminated part of the turn, the SB is rotated around the transverse axis of rotation of the SB to the intersection of the straight line passing through the surface of the radiator-radiator facing the Sun and directed to the Sun with the SB and the SB is rotated around the longitudinal axis of rotation of the SB until the angle is reached between the normal to the working surface of the SB and the direction to the Sun of the minimum value. With this orientation, the SB panel obscures the surface area of the radiator-heat radiator facing the Sun. Moreover, the rotation of the SB around the longitudinal axis of rotation of the SB until the angle between the normal to the working surface of the SB and the direction to the Sun reaches the minimum value simultaneously serves both to increase the area shaded by the SB and to maximize the generation of electricity (electricity generation depends on the angle of incidence of solar radiation on SB surface). These turns of the SB perform during the total duration Δ:

$$\Delta =k\cdot P-T,\text{(eleven)}$$

and within the time interval [t ₁ , t ₂ ], the start and end times of which are calculated by the formulas:

$$t_{\mathrm{one}}=t_S+\frac{\mathrm{<figure-callout\; id="2"\; label="P"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">P</figure-callout>}}{2\cdot \pi }(\eta -\gamma ),\text{(12)}$$

$${\mathrm{<figure-callout\; id="2"\; label="t"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">t</figure-callout>}}_2=t_S+\frac{\mathrm{<figure-callout\; id="2"\; label="P"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">P</figure-callout>}}{2\cdot \pi }(\eta +\pi +\gamma ),\text{(13)}$$

Where $$\gamma =\arcsin \frac{L^2-D^2-{\mathrm{<figure-callout\; id="2"\; label="E"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">E</figure-callout>}}^2\cdot \mathrm{<figure-callout\; id="2"\; label="c\; t\; g"\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">c\; </figure-callout>}t{g}^{}{}^2\mathrm{<figure-callout\; id="2"\; label="\beta "\; filenames="00000018.png,00000019.png"\; state="\{\{state\}\}">\beta </figure-callout>}}{2\cdot D\cdot E\cdot ctg\beta },\text{(fourteen)}$$

t _s is the instant of passage of the spacecraft of the sunflower point of the revolution,

L is the length of the SB along the longitudinal axis of rotation of the SB, counted from the transverse axis of rotation of the SB,

D is the distance from the transverse axis of rotation of the SB to the farthest point from the axis of the surface of the radiator-radiator,

E is the distance from the plane of rotation of the SB to the farthest point from the plane of the surface of the radiator-radiator,

β is the angle between the direction to the Sun and the orbital plane of the spacecraft.

The distance E can be counted along the transverse axis of rotation of the SB. In this case, this distance can be defined as the distance between the longitudinal axis of rotation of the SB and the perpendicular to the transverse axis of rotation of the SB passing through the surface point of the radiator-heat emitter farthest from the plane of rotation of the SB.

If there is no shadow part on the coil in relation (11), the duration of the shadow part of the coil is zero (T = 0).

The interval [t ₁ , t ₂ ] is obtained in such a way that at any moment of this time interval the SB can be rotated to a position in which a straight line directed from the surface area of the radiator-heat emitter facing the Sun towards the Sun directly intersects the SB panel - t .e. SB will obscure this area of the surface of the radiator-heat emitter. Outside the time interval [t ₁ , t ₂ ], the length of the SB L is, in general, not enough for the surface of the heat sink to be obscured by the SB.

Thus, as a result of performing the described actions in total on the coil, taking into account the duration of the shadow part of the coil T, the radiator-heat emitter will be shaded for a time Δ + T = k · P, which is the necessary duration of the heat release time on the coil.

Let us explain the formulas used.

Relations (12), (13), (14) are obtained from the relation:

$$L=D+E\cdot tg\left(\frac{\pi }{2}-\beta \right).\text{(fifteen)}$$

Let us explain relation (15). To do this, we consider such a rotated position of the longitudinal axis of rotation of the SB, in which a straight line passing through a point of the surface area of the radiator-heat emitter facing the Sun and directed to the Sun intersects the longitudinal axis of rotation of the SB.

Relation (15) defines points А ₁ , А ₂ on the orbit of the orbit such that for an angle between the direction to the Sun and the orbital plane of the spacecraft equal to β, and for the above-turned position of the longitudinal axis of rotation of the SB, the straight line passing through the point of the region facing the Sun surface of the radiator-heat emitter and directed to the Sun passes through the end of the SB. This means that the length of the SB L corresponds to the length necessary and sufficient for shading the surface of the heat sink radiator panel SB at the points of turn A ₁ , A ₂ (figure 2).

Geometrically, the position of these points A ₁ , A _{2 is} described by the following angles: points A ₁ , A ₂ are separated from point A _s along the orbital motion of the spacecraft by the angles η-γ and η + π + γ, respectively (Fig. 1). Whence formulas (12), (13) follow.

At all points of the orbit located along the spacecraft’s orbital flight between points A ₁ , A ₂ (for example, at point A in FIG. 1, FIG. 3), the SB panel has a sufficiently short SB length than the SB length to obscure the surface of the heat sink radiator necessary and sufficient for shading the surface of the heat sink at the points A ₁ , A ₂ .

Thus, at all points of the orbit located along the spacecraft’s orbital flight between points between points A ₁ , A ₂ defined by relation (15), the SB length L will be sufficient to obscure the radiator-radiator by the SB panel.

On the other hand, at the turn points located along the spacecraft’s orbital flight between points A ₂ , A ₁ (for example, at point A ₃ in FIG. 1, FIG. 4), a large SB length is required to obscure the surface of the heat-radiator by the SB panel than the length of the SB, necessary and sufficient for shading the surface of the radiator-radiator at points A ₁ , A ₂ - i.e. the length of the SB L is, in general, insufficient for the surface of the heat sink to be obscured by the SB between points A ₂ -A ₃ -A ₁ .

Note that figure 1 ÷ 4 presents illustrations in which the distance from the transverse axis of rotation of the SB to the farthest point from the axis of the radiator-heat emitter D is AC, A ₁ C ₁ , A ₂ C ₂ , A ₃ C ₃ , and the distance from the plane of rotation of the SB to the farthest point of the radiator-radiator E is equal to AB, A ₁ B ₁ , A ₂ B ₂ , A ₃ B ₃ . In the general case, D≥AC, A ₁ C, A ₂ C ₂ , A ₃ C _3, and E≥AB, A ₁ B ₁ , A ₂ B ₂ , A ₃ B ₃ .

Relations (5) ÷ (9) are illustrated by the diagram shown in Fig. 5, while relation (9) corresponds to the equality of the duration of the shadow part of the turn of the necessary duration of the time of heat release by the heat sink-radiator on the turn.

Relations (2), (3) follow from (6) ÷ (9) for, respectively,

β * = β _max and β * = 0.

As a rule, several satellites and several heat sinks are placed on the spacecraft. For example, SBs can be installed in pairs, while in each pair the longitudinal axis of rotation of the SBs are directed in opposite directions. Several (for example, at least four) radiators, heat emitters, each of which has a flat shape, can be placed on different sides of the outer surface of the spacecraft. In this case, the actions of the proposed method are applied to various various combinations of SB and radiators, heat emitters.

We describe the technical effect of the invention.

The proposed technical solution provides an increase in the functioning efficiency of the radiator-heat radiator located on a spacecraft equipped with mobile SB by creating additional conditions for the natural cooling of the radiator-heat radiator by shading its SB SC at any altitude of the spacecraft’s orbital orbit.

The achievement of the technical result is ensured by:

- completing the construction of the proposed orbital orientation of the spacecraft, in which the plane of rotation of the SB is oriented in the proposed manner,

- determining the proposed angles and orbit heights, by which the orbit is determined by the proposed method, at which the condition for achieving the required duration of natural cooling of the radiator-heat emitter in the shadow of the planet is violated, and the time interval within which the proposed SB rotations are carried out is determined,

- execution on the proposed orbit of the orbit of the proposed turns of the SB during the proposed duration of time and within the proposed time interval.

As a result of the proposed actions and the proposed conditions for their implementation, it is possible to implement the shading of the radiator-heat radiator of a rotating SB, which creates the conditions for the natural cooling of the radiator-heat radiator (when there is no illumination of the radiator-heat radiator by the Sun). An assessment of the effectiveness of the application of the invention on the International Space Station (ISS) showed that its use will qualitatively increase the efficiency of the functioning of radiators-heat emitters located on the modules of the Russian segment of the ISS.

Industrial execution of the essential features characterizing the invention is not complicated and can be performed using known technologies.

Claims (1)

A method of controlling an orbiting spacecraft, including performing an orbital flight of a spacecraft with a radiator-heat emitter placed on it in an orbit around the planet and turning a solar battery installed with two degrees of freedom on a spacecraft into a working position corresponding to combining the normal to the working surface of the solar battery with direction to the Sun, characterized in that they build the orbital orientation of the spacecraft, in which the plane of rotation of the sun of the primary battery is parallel to the orbit plane of the spacecraft, and the solar battery is located relative to the orbit plane from the side of the Sun, the maximum value of the angle between the velocity vector of the spacecraft and the perpendicular to the transverse axis of rotation of the solar battery passing through the surface of the radiator-heat radiator is determined, the angle between the direction to the Sun is determined and the plane of the orbit of the spacecraft, determine the height of the orbit of the spacecraft, by a certain height of the orbit and a certain value The angle between the direction to the Sun and the orbital plane of the spacecraft is determined by the orbits of the orbit on which the duration of the illuminated part of the orbit exceeds the difference between the period of revolution of the spacecraft and the required length of time for the heat to be released by the radiator-radiator on the orbit, and on the above orbits of the orbit when the spacecraft passes through the illuminated part turn rotate the solar battery around the transverse axis of rotation of the solar battery until the intersection of a straight line passing through The area of the surface of the radiator-heat radiator and directed towards the Sun, with the solar battery, and the rotation of the solar battery around the longitudinal axis of rotation of the solar battery until the angle between the normal to the working surface of the solar battery and the direction to the Sun reaches the minimum value, the rotations of the solar battery described above are performed for total duration k · Р-Т within the time interval, the start and end moments of which are calculated, respectively, according to the formulas:

Where

k is a coefficient characterizing the required length of time for heat release by the heat sink-radiator at each turn and equal to the ratio of the necessary duration of time for heat release on the turn to the duration of the turn,
P is the period of revolution of the spacecraft,
T is the duration of the shadow part of the coil,
t _s is the time moment of the spacecraft passing the sunflower point of the revolution,
η is the maximum value of the angle between the velocity vector of the spacecraft and the perpendicular to the transverse axis of rotation of the solar battery passing through the surface of the heat sink,
L is the length of the solar battery along the longitudinal axis of its rotation,
D is the distance from the transverse axis of rotation of the solar battery to the farthest point from the axis of the surface of the radiator-radiator,
E is the distance from the plane of rotation of the solar battery to the farthest point from the plane of the surface of the surface of the radiator-heat radiator,
β is the angle between the direction to the Sun and the plane of the orbit of the spacecraft.

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