Method of controlling orbiting spacecraft

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.

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The invention relates to the field of space technology and can be used to control the motion of the SPACECRAFT).

The SPACECRAFT is equipped with solar batteries (SB), which produce electricity for the functioning of the AC. When you implement flight operations KA activated side apparatus, the elements of which when the work is heated. The heat is used for temperature control of SPACECRAFT, and its excess is discharged into the surrounding SPACECRAFT space through the radiators-emitters. The amount of heat the most effective on shadow earth orbit, during which the entire surface of the radiator-teplocluchenka not exposed to direct solar radiation, and less effective on the sunlit portions of the orbit, when the reset heat comes mainly from those portions of the radiator-teplocluchenka that shaded components KA (Tabor O. N., Kadaner J. C. Questions of heat transfer in space. M.: Higher school, 1972).

Known way to control the orbital SPACECRAFT (Eliseev A. S. Technology of space flight. M: mechanical engineering, 1983), including the reversal SAT in the working position of the Sun and the running of the orbital flight of a SPACECRAFT around a planet in which the reset heat heat sink-teploizolyatsii is in moments of finding KA in the shadow of the planet, and in moments vetovo part of the coil, when the current orientation of the SPACECRAFT design SPACECRAFT obscures the radiator teploizolyatsii from direct sunlight. In this way the reset heat heat sink-teploizolyatsii is due to the natural cooling radiator-teplocluchenka in the moments of its shades of the planet or structures CA. The disadvantage of this method is that it is, in General, does not guarantee the presence of the luminous part of the orbit shading radiator-teplocluchenka design of the SPACECRAFT. For example, when the SPACECRAFT into solar orbit (when the shadow on the orbit the orbit is missing) no shading radiator-teplocluchenka design KA means no shading radiator-teplocluchenka throughout the circuit, which significantly reduces the effectiveness of the radiator-teploizolyatsii its functions.

Known way to control the orbital SPACECRAFT (Malozemov centuries heating mode of the spacecraft. M.: Mashinostroenie, 1980) adopted for the prototype, including the execution of orbital flight SPACECRAFT around the planet, turn SA into position on the Sun and run turn the AC up to Shader radiator-teplocluchenka design of the SPACECRAFT. This method is guaranteed reset heat heat sink-teploizolyatsii due to natural cooling radiator-teplocluchenka at moments of shading design is the Ktsia KA.

Prototype method has a major drawback - to create conditions for natural cooling radiator-teplocluchenka due to shading design KA in this way it is necessary to continuously perform the above special turn of SPACECRAFT that, on the one hand, requires additional energy costs for its implementation, and on the other hand, the implementation of the above special turn of SPACECRAFT in the General case can be contrasted with the construction of the desired target orientation KA-the orientation, which must be KA to solve his targets. Thus, in the process of decision targets KA, which is accompanied by the construction of the desired target orientation of the SPACECRAFT, in the General case, not created conditions for natural cooling radiator-teplocluchenka due to its shading, which impairs the efficiency of the radiator-teplocluchenka.

Task to be solved by the present invention is directed, is the efficiency of the radiator-teplocluchenka installed on the SPACECRAFT, with moveable SAT.

Technical result achieved in the implementation of the present invention is the creation of additional conditions for natural cooling radiator-teplocluchenka due to shading his mobile SA is A.

The technical result is achieved in that in the method of controlling an orbiting SPACECRAFT, including the execution of orbital flight SC posted on the radiator-teploizolyatsii in orbit around the planet and turn SB installed with two degrees of freedom on the SPACECRAFT, in its working position, corresponding to the combination of the normal to the working surface SB with direction to the Sun, additionally build the orbital orientation of the SPACECRAFT during which the rotation plane SAT parallel to the plane of the orbit of the SPACECRAFT and SB is located relative to the plane of the orbit of the Sun, determine the maximum value of the angle between the velocity vector of the SPACECRAFT and perpendicular to the transverse axis of rotation of the SAT, passing through the surface of the radiator-teplocluchenka, determine the angle between the direction of the Sun and the plane of the orbit, determine the height of the orbit, the altitude of the orbit and a particular value of the angle between the direction of the Sun and the plane of the orbit determines the coils of the orbit on which the duration of the illuminated side of the coil exceeds the difference between the orbital period of the AC and the necessary duration of the reset time of the heat radiator-teploizolyatsii on the circuit, and videopreteen orbits the orbit by passing KA illuminated side of the coil do turn SAT around a transverse axis of rotation SAT before crossing the nternet, passing through the sunward surface area of the radiator-teplocluchenka and aimed at the Sun to SAT and turn SAT around the longitudinal axis of rotation of the SAT until the angle between the normal to the working surface SB and the direction to the Sun the minimum value, the above turns SB perform during the total duration of the k·P-T within the time interval, the start and end of which are calculated, respectively, by the formulas:

$$t_1=t_S+\frac{P}{2\cdot \pi }(\eta -\gamma ),t_2=t_S+\frac{P}{2\cdot \pi }(\eta +\pi +\gamma ),$$

where$$\gamma =\arcsin \frac{L^2-D^2-E^2\cdot ct{g}^2\beta }{2\cdot D\cdot E\cdot ctg\beta },$$

k - coefficient characterizing the required duration of the reset time heat radiator teploscat the LEM at each point is equal to the ratio of necessary duration of the reset time of heat on the circuit for the duration of the round,

P is the orbital period of the SPACECRAFT,

T - the duration of the shadow part of the round,

t_s- time passing KA sunflower point round,

η is the maximum value of the angle between the velocity vector of the SPACECRAFT and perpendicular to the transverse axis of rotation SB passing through the surface of the radiator-teplocluchenka, the positive direction of the reference angle of the velocity vector in the direction of the radius vector KA,

L - length SAT along the longitudinal axis of its rotation,

D is the distance from the transverse axis of rotation of the SAT to the most remote from the axis point of the surface of the radiator-teplocluchenka,

E - the distance from the plane of rotation of the SAT to the most remote from the plane surfaces of the radiator-teplocluchenka,

β is the angle between the direction of the Sun and the plane of the orbit.

The essence of the invention is illustrated in Fig.1÷5, which shows: Fig.1 - scheme of the mutual position of SB and radiator-teplocluchenka relative to the direction of the Sun, illustrating a view in the plane of the orbit, Fig.2, 3, 4 - scheme of the mutual position of SB and radiator-teplocluchenka relative to the direction of the Sun, illustrating end view of the orbital plane of Fig.5 is a diagram illustrating the definition of the angle between the direction of the Sun and the plane of the orbit, in which the duration of the shadow part of the loop orbit is not the required time duration of the reset heat heat sink-teploizolyatsii on the circuit.

In Fig.1÷5 introduced the notation:

1 - orbit SATELLITES;

2 - longitudinal axis of rotation of the SAT;

3 is transverse the axis of rotation of the SAT;

4 - radiator-teploizolyatsii;

5 is perpendicular to the transverse axis of rotation SB passing through the sunward surface area of the radiator-teplocluchenka,

6 is a plane of rotation of the SAT;

S is the direction vector of the Sun;

S_pthe projection direction of the Sun on the plane of the orbit;

About the center of the planet;

β is the angle between the direction of the Sun and the plane of the orbit;

A_s- the position of the SPACECRAFT in sunflower point orbits;

And₁And₂position the SPACECRAFT in moments of t₁, t₂;

AC, A₁C₁, A₂C₂, A₃C₃- the distance from the transverse axis of rotation of the SAT to the most remote from the axis point sunward surface area of the radiator-teplocluchenka;

AB, A₁B₁And₂In₂And₃In₃.- the distance from the plane of rotation of the SAT to the most remote from the plane of the point sunward surface area of the radiator-teplocluchenka;

VM₁M₁In₂M₂In₃M₃- cut longitudinal axis of rotation of the SAT concluded between the beginning and the end of the SAT;

F₁F₂position the SPACECRAFT at the beginning and end of the shadow area of a coil;

F_s- state the SPACECRAFT at the time of the middle of the shadow area of a coil;

The Z - surface of the planet.

Explain proposed mode of action.

Accept that KA SA established with two degrees of freedom: the panel SAT rotated around a longitudinal axis of rotation and SAT around a transverse axis of rotation of the SAT. And turn SAT around a transverse axis of rotation of the SAT is to rotate the longitudinal axis of rotation SAT around a transverse axis of rotation of the SAT. Thus consider a system of position control of the security Council, in which the transverse axis of rotation SAT directly passes through the longitudinal axis of rotation and SAT perpendicular to it.

Accept that SB made opaque: SAT delay coming to them, the flow of solar energy and can shade yourself from the Sun the external surface of the SPACECRAFT.

Accept that SB have an elongated rectangular shape, and the length of the SAT measured along the longitudinal axis of rotation of the SAT. The width SB is not less than the value of the linear dimension of the surface of the radiator-teplocluchenka.

In the proposed method performs orbiting SPACECRAFT to host radiator-teploizolyatsii around the planet in near-circular orbit.

Perform the reversal SAT in working position, corresponding to the combination of the normal to the working surface SB with direction to the Sun. In this orientation SB provides the maximum advent of electricity is.

Build the orbital orientation of the SPACECRAFT during which the rotation plane SAT parallel to the plane of the orbit of the SPACECRAFT and is located relative to the plane of the orbit from the Sun. This corresponds to a transverse axis of rotation SAT perpendicular to the plane of the satellite orbit, and SB is located relative to the plane of the orbit of the Sun.

After building the orbital orientation perform its maintenance and determine the maximum value of the angle η between the velocity vector of the SPACECRAFT and perpendicular to the transverse axis of rotation SB passing through the surface of the radiator-teplocluchenka, the positive direction of the reference angle η of the velocity vector in the direction of the radius vector of the SPACECRAFT.

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

Determine the height of the orbit N.

For certain values of the angle between the direction of the Sun and the plane of the orbit of β and the orbit altitude H determine (select) the coils of the orbit on which the duration of the illuminated side of the coil exceeds the difference between the orbital period of the AC and the necessary duration of the reset time of the heat radiator-teploizolyatsii on the circuit (data coils are not able to ensure the required duration of natural cooling radiator-teplocluchenka in the shadow of the planet).

Definition (selection of such coils is for example, as follows.

When the current altitude of the orbit of the SPACECRAFT in the altitude range [H₁H₂]:

$$H_1\le H\le H_2,\text{(1)}$$

$$H_1=\frac{R}{\sin \left(\arccos \left(\cos (k\cdot \pi )\cdot \cos {\beta }_{\max }\right)\right)}-R,\text{(2)}$$

$$\begin{array}{l}{H}_2=\frac{R}{\sin (k\cdot \pi )}-R,\text{(3)}\\ \end{array}$$

$$\beta \max =\min \left\{\left|i\right|+\epsilon ,\frac{\pi }{2}\right\},\text{the (4)}$$

where k is the coefficient characterizing the required duration of the reset time of the heat radiator-teploizolyatsii at each point is equal to the ratio of necessary duration of the reset time of heat on the circuit for the duration of the round,

R is the radius of the planet,

β_max^_the maximum value that can take the angle between the direction of the Sun and the plane of the orbit,

i is the inclination angle of the orbit KA,

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

select only the coils in which the current value of the angle between the direction of the Sun and the plane of the orbit more β values β*, in which the duration of the shadow part of the loop orbit is equal to the required duration of the reset time of the heat radiator-teploizolyatsii on stage:

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

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

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

$$\lambda =\frac{T}{2}\cdot \frac{2\cdot \pi }{P},\text{(8)}$$

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

where θ is the angular polarstar visible with the AC drive of the planet,

λ is the angular polarstar shadow part of the round orbit, measured from the center of the planet,

P is the orbital period of the SPACECRAFT,

T - the duration of the shadow part of the loop.

Condition (5) corresponds to the fact that the length of the shadow part of these orbits the orbit is less than the required duration of the reset time of the heat radiator-teploizolyatsii on the circuit. If the condition (5) shadow on the circuit or missing entirely, or its duration is less than the required time duration of discharge of heat, R is Diatron-teploizolyatsii on the circuit. If the condition (5) is not performed (when (β≤β*), then at this stage the length of the shadow part of the coil is greater than or equal to the required duration of the reset time of the heat radiator-teploizolyatsii on the circuit.

At the current height of the orbit is greater than the height H₂:

$$H_2<H,\text{(10)}$$

select all the coils, because when running (10) shadow on all the turns or missing, or its duration is less than the required duration of the reset time of the heat radiator-teploizolyatsii on the circuit.

At the current height of the orbit is less than the height H₁(if N<N₁), at any stage there is a shadow part and its duration is always more necessary duration of the reset time of the heat radiator-teploizolyatsii on the circuit.

On the selected coils of the orbit by passing KA illuminated side of the coil do turn SAT around a transverse axis of rotation of the SAT to the intersection of the line passing through the sunward surface area of the radiator-teplocluchenka and aimed at the Sun to SAT and turn SAT around the longitudinal axis of rotation of the SAT until the angle between the normal to the working surface SB and the direction is by giving the Sun the minimum value. In this orientation, the panel SAT shadows facing the Sun, the surface area of the radiator-teplocluchenka. In this case, rotation SAT around the longitudinal axis of rotation of the SAT until the angle between the normal to the working surface SB and the direction to the Sun the minimum value is used both to increase the area, shaded SAT, and to maximize the generation of electricity generation of electricity depends on the angle of incidence of solar radiation on the surface of the SAT). Data turns SB perform during the total duration Δ:

$$\Delta =k\cdot P-T,\text{(11)}$$

and within time interval [t₁, t₂], the moments of the beginning and end of which are calculated by the formulas:

$$t_1=t_S+\frac{P}{2\cdot \pi }(\eta -\gamma ),\text{(12)}$$

$$t_2=t_S$$

where$$\gamma =\arcsin \frac{L^2-D^2-E^2\cdot ct{g}^2\beta }{2\cdot D\cdot E\cdot ctg\beta },\text{(14)}$$

t_s- time passing KA sunflower point round,

L - length SAT along the longitudinal axis of rotation of the SAT, measured from the transverse axis of rotation SAT,

D is the distance from the transverse axis of rotation of the SAT to the most remote from the axis point of the surface of the radiator-teplocluchenka,

E - the distance from the plane of rotation of the SAT to the most remote from the plane surfaces of the radiator-teplocluchenka,

β is the angle between the direction of the Sun and the plane of the orbit.

The distance E can be counted along the transverse axis of rotation of the SAT. In this case, this distance can be defined as the distance between the longitudinal axis of the treatment of the security Council and perpendicular to the transverse axis of rotation of the SAT, passing through the most remote from the plane of rotation of the SAT point of the surface of the radiator-teplocluchenka.

In the absence of a shadow on the circuit side in equation (11) the duration of the shadow part of the loop is equal to zero (T=0).

The interval [t₁, t₂] obtained in such a way that at any moment this time interval SB can be rotated to a position in which a straight line directed from the sunward surface area of the radiator-teplocluchenka towards the Sun, crosses the panel SB - i.e., the SAT will overshadow the surface area of the radiator-teplocluchenka. Outside the time interval [t₁, t₂] length SB L, in General, not enough to the surface of the radiator-teplocluchenka could be shaded SAT.

Thus, the result of performing the above steps, the total on the circuit, taking into account the duration of the shadow part of round T, the radiator teploizolyatsii will be shaded during the time Δ+T=k·R, which is the required duration of the reset time of heat on the circuit.

Explain the formulas used.

Ratio(12), (13), (14) obtained from the relation:

$$L=D+E\cdot tg\left(\frac{\pi }{2}-\beta \right).\text{the (15)}$$

Explain the relation (15). To do this, let us consider the rotated position of the longitudinal axis of rotation of the SAT, which line passes through the point sunward surface area of the radiator-teplocluchenka and aimed at the Sun, intersects the longitudinal axis of rotation of the SAT.

Equation (15) determines in turn orbits a₁And₂such that when the angle between the direction to the Sun and the plane of the orbit, is equal to the value of β, and in such rotated position of the longitudinal axis of rotation of the SB line passing through the point sunward surface area of the radiator-teplocluchenka and aimed at the Sun, passes through the end of SAT. This means that the length SB L corresponds to the length which is necessary and sufficient for shading the surface of the radiator-teplocluchenka panel SAT at points round And₁And₂(Fig.2).

Geometrically the position of data points And₁And₂described by the following angles: a₁And₂distance from point A_sin the course of the orbital motion of the SPACECRAFT at the corners, respectively, η γ, η+π+γ (Fig.1). Where there is a formula(12), (13).

At all points of a coil located along the orbital flight of KA between points a₁And₂(for example, at point a in Fig.1, figs.3), for shading the surface radiation is ora-teplocluchenka panel SAT quite smaller length SAT, than the length of the security Council, are necessary and sufficient to shade the surface of the radiator-teplocluchenka at points a₁And₂.

Thus, at all points of a coil located along the orbital flight of KA between points between points a₁And₂defined by the relation (15), length SB L will be enough to shade radiator-teplocluchenka panel SAT.

On the other hand, at the points of a coil located along the orbital flight of KA between points a₂And₁(for example, at point a₃in Fig.1, figs.4), for shading the surface of the radiator-teplocluchenka panel SAT requires a large length of the SAT than the length of the security Council, are necessary and sufficient to shade the surface of the radiator-teplocluchenka at points a₁And₂- i.e. length SB L, in General, not enough to the surface of the radiator-teplocluchenka could be shaded SAT between points a₂-A₃-A₁.

Note that in Fig.1÷4 presents illustrations, in which the distance from the transverse axis of rotation of the SAT to the most remote from the axis point of the radiator-teplocluchenka D is equal to AC, A₁C₁And₂With₂And₃With₃and the distance from the plane of rotation of the SAT to the most remote from the plane of the point of the radiator-teplocluchenka E is the AB₁In₁And₂B₂And_{3 In3. In the General case D≥AC, A1C And2With2And3With3and E≥AB, A1B1And2In2And3In3.}

Ratio (5)÷(9) are illustrated by the scheme shown in Fig.5, the ratio (9) corresponds to the equality of the length of the shadow part of the revolution necessary duration of the reset time of the heat radiator-teploizolyatsii on the circuit.

The relation (2), (3) follow from (6)÷(9), respectively,

β*=β_maxand β*=0.

Usually on KA post some SS and some radiators-emitters. For example, SA can be installed in pairs, with each pair of the longitudinal axis of rotation SAT in opposite directions. A few (for example, not less than four radiators-emitters, each of which has a flat shape, can be placed on different sides of the external surface of the SPACECRAFT. In this case, the validity of the proposed method is applied to all sorts of different combinations and SAT radiators-emitters.

Describe the technical effect of the invention.

The proposed solution improves the efficiency of the functioning of the radiator-teplocluchenka placed on with moveable SB KA, by creating additional conditions for natural cooling radiator-teplocluchenka by Satan is that its SB KA at any height near-circular orbit.

The achievement of the technical result is achieved through:

- complete construction of the proposed orbital orientation of the SPACECRAFT in which the plane of rotation SB focus suggested by the way,

the proposed definition of angles and height of the orbit on which the proposed method determines the coils of the orbit, which violates the condition for achieving the desired duration of natural cooling radiator-teplocluchenka in the shadow of the planet, and the proposed manner is determined by the time interval within which are proposed twists SAT,

- perform the proposed orbits the orbit of the proposed SB turns over the proposed duration of time and within the proposed time interval.

Consequently, the proposed action and the proposed terms of their implementation, it is possible to implement shading radiator-teplocluchenka rotating security Council, which creates conditions for natural cooling radiator-teplocluchenka (in moments of lack of lighting-radiator-teplocluchenka the Sun). Evaluated the effectiveness of the present invention on the international space station (ISS) has shown that its use will improve the efficiency of the radiators-emitters placed on the modules Ross is isogo segment of the ISS.

An industrial implementation of essential features that characterize the invention, is not difficult and can be performed by known technologies.

The method of controlling the orbital spacecraft, including the execution of orbital flight of a spacecraft placed on it by the radiator-teploizolyatsii in orbit around a planet and the reversal of the solar panels mounted with two degrees of freedom on the spacecraft, in its working position, corresponding to the combination of the normal to the working surface of the solar battery with the direction to the Sun, characterized in that build orbital orientation of the spacecraft in which the plane of rotation of the solar panels parallel to the plane of the orbit of the spacecraft and the solar panel is located relative to the plane of the orbit of the Sun, determine the maximum value of the angle between the velocity vector of the spacecraft and perpendicular to the transverse axis of rotation of the solar battery, passing through the surface of the radiator-teplocluchenka, determine the angle between the direction of the sun and the orbit plane of the spacecraft, determine the height of the orbit of the spacecraft, at a certain altitude and a particular value of the angle between the direction of the Sun and the plane of the orbit to the body of low unit determines the coils of the orbit, where the duration of the illuminated side of the coil exceeds the difference between the orbital period of the spacecraft and the necessary duration of the reset time of the heat radiator-teploizolyatsii on the circuit, and videopreteen orbits the orbit by passing spacecraft illuminated side of the coil perform the rotation of the solar battery around a transverse axis of rotation of the solar battery to the intersection of the line passing through the sunward surface area of the radiator-teplocluchenka and aimed at the Sun, with solar battery and rotating solar panels around the longitudinal axis of rotation of the solar panels until the angle between the normal to the working surface of the solar battery and the direction to the Sun the minimum value, the above turns solar panels perform during the total duration of the k·P-T within the time interval, the start and end of which are calculated, respectively, by the formulas:

where
k - coefficient characterizing the required duration of the reset time of the heat radiator-teploizolyatsii at each point is equal to the ratio of necessary duration of the reset time of heat on the circuit for the duration of the round,
P is the orbital period of the spacecraft,
T - glutelin is here the shadow part of the revolution,
t_s- the time passing by the spacecraft seed point round,
η is the maximum value of the angle between the velocity vector of the spacecraft and perpendicular to the transverse axis of rotation of the solar battery, passing through the surface of the radiator-teplocluchenka,
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 panels to the most remote from the axis point of the surface of the radiator-teplocluchenka,
E - the distance from the plane of rotation of the solar panels to the most remote from the plane surfaces of the radiator-teplocluchenka,
β is the angle between the direction of the sun and the orbit plane of the spacecraft.