Control over orbital spacecraft

FIELD: aircraft engineering.

SUBSTANCE: invention relates to in-flight control over spacecraft equipped with heat radiator and solar battery. Proposed process comprises spacecraft flight in orbit around the planet with solar battery turn to position corresponding to normal to solar battery working surface directed to the Sun. Spacecraft orbital orientation is constructed whereat solar battery spinning plate is parallel with spacecraft orbit plane while solar battery is located on the Sun side relative to orbit plane. Spacecraft orbit altitude and angle between direction to the Sun and spacecraft orbit plane are defined. Magnitude of said angle (β*) is defined whereat duration of turn shadow section equals the necessary time of radiator heat release in said turn. Orbit turns are defined wherein current magnitude of said angle is larger than β*. In said turns, solar battery is turned around crosswise and lengthwise rotation axes unless shadowing of solar battery radiator. Note here that minimum departure of orientation of solar battery working surface to the Sun. Spacecraft orbital flight is conducted in near-circle orbit at altitude not exceeding a definite design value.

EFFECT: higher efficiency of radiator with solar battery shadowed at whatever position of spacecraft on orbit turn.

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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. Moscow, Higher school", 1972).

Known way to control the orbital SPACECRAFT (Eliseev A. S. Technology of space flight. Moscow, Mashinostroyeniye, 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 t is the train in moments of luminous 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. Moscow, Mashinostroyeniye, 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 in moments his satistically 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, SBCA.

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 angle between the direction of the Sun and the plane of the orbit, determine the height of the orbit, at a certain height of the orbit determines the value of the angle between the direction of the Sun and the plane of the orbit 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 the circuit, determine the turns of the orbit on which the current value of the angle between the direction of the Sun and the plane of the orbit more videopreteen values of β^*and videopreteen orbits orbits 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 Sol is CE, with SB 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 when passing KA-lit part of the orbits, and orbital flight KA perform at near-circular orbit with a height not more than

,

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,

P is the orbital period of the SPACECRAFT,

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

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,

R is the radius of the planet.

The essence of the invention is illustrated in Fig.1, 2, 3, are presented: 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 - scheme of the mutual position of SB and radiate the a-teplocluchenka relative to the direction of the Sun, illustrating end view of the orbital plane of Fig.3 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 equal to the required duration of the reset time of the heat radiator-teploizolyatsii on the circuit.

In Fig.1, 2, 3 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;

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

A And₁position the SPACECRAFT in orbit orbit;

AU is 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 is 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;

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

F₁F₂position the SPACECRAFT at the beginning of iconza shadow area of a coil;

F_s- the position of 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 around the planet in near-circular orbit, altitude which N does not exceed the value of H_maxcalculated by the formula:

where k is a coefficient characterizing the mu is necessary 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,

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,

R is the radius of the planet.

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 rotation of the security Council and perpendicular to the transverse axis of rotation SAT through the most remote from the plane of rotation of the SAT point on the surface of the radiator-teplocluchenka.

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 arrival power.

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.

Determine the angle between the direction of the Sun the plane of the orbit of β (accept, it is always β≥0).

Determine the height of the orbit N.

Determine the value of the angle between the direction of the Sun and the plane of the orbit 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 the circuit. The definition of this angle can be made according to the formula:

Angle definition (3) mathematically can be performed only when the height of the orbit is not less than the value of N^*calculated by the formula:

where 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').

Determine the turns of the orbit on which the current value of the angle between the direction of the Sun and the plane of the orbit of β more videopreteen values of β^*:

Condition (7) 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 (7) a shadow on the circuit or missing entirely, or its duration is less than the required permanent the particular time reset heat heat sink-teploizolyatsii on the circuit. If the condition (7) 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 altitudes orbit smaller than the height H^*(if N<N^*), at any stage there is the shadow of revolution and its duration is always more necessary duration of the reset time of the heat radiator-teploizolyatsii on the circuit.

On videopreteen orbits orbits (7) when 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 to 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 the solar radiation on the surface of the SAT).

Data turns SB perform during the total duration Δ:

where P is the orbital period of the SPACECRAFT,

T - the duration of the shadow part of the loop (on the sun orbits T=0).

Condition (2) corresponds to the fact that at any point in the orbit of a given height when the AC in the above orbital orientation of the longitudinal axis of rotation of the SAT 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 SAT.

Thus throughout the round, taking into account the duration of his shadow side, radiator teploizolyatsii is guaranteed to be shaded from the Sun during the time Δ+T=k·P, which is the required duration of the reset time of heat on the circuit.

Execution orbiting SPACECRAFT around the planet in near-circular orbit, the height of which does not exceed the given value, provided you perform the necessary maneuvers of the SPACECRAFT. For example, for this purpose can be applied scheme of maneuver of the SPACECRAFT, used to control the flight of the international space station (ISS) and transport spacecraft "Soyuz" and "Progress" and other

Explain the formulas used.

Ratio (1), (2) are obtained from the expressions (3), (7) and ratios:

Explain the formula (9). To do this, consider the point of revolution, in which, while maintaining the above orbital orientation of the SPACECRAFT perpendicular to the transverse axis of rotation SB passing through point sunward surface area of the radiator-teplocluchenka 5, the parallel projection of the solar direction in the plane of the orbit (the position of the SPACECRAFT at point a in Fig.1).

Consider also this rotated position, the longitudinal axis of rotation of the security Council, in which the longitudinal axis of rotation SAT parallel projection of the solar direction in the plane of the orbit (position VM longitudinal axis of rotation of SB in Fig.1).

Condition (9) means that in the described point a round orbit when the angle between the direction to the Sun and the plane of the orbit, is equal to the value of β, and described in the rotated position VM longitudinal axis of rotation of the SB line passing through the point sunward surface area of the radiator-teplocluchenka and aimed at the Sun directly intersects a segment of the VM to the longitudinal axis of rotation of the SAT concluded between the beginning and the end of SAT. This is equivalent to the fact that the length SB L enough to shade radiator-teplocluchenka panel SAT.

In all other points of the orbit (for example, the position of the SPACECRAFT at the point A₁in Fig.1) for shading radiator-teplocluchenka panel SAT quite less dliness, than the length of the SA required for shading radiator-teplocluchenka described in the point round.

Thus, if in the described point of the loop condition (9), and also in all other points on this round of the length of the SAT will be enough to shade radiator-teplocluchenka panel SAT.

Note that in Fig.1, 2 shows the illustration, in which 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 D is equal to the speakers and the distance from the plane of rotation of the SAT to the most remote from the plane surfaces of the radiator-teplocluchenka E is equal to AB. In the General case D≥AC and E≥AB.

The relation (3) is obtained from the following formulas illustrated in Fig.3:

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.

Equation (13) corresponds to the condition of equality of the length of the shadow part of the coil and the necessary duration of the reset time of the heat radiator-teploizolyatsii on the circuit.

Relations (4), (5) follow from the relation:

As a rule, KA place SAT a few and several is like 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 due to its shading SAT in any location of the SPACECRAFT at the current stage of the orbit.

The achievement of the technical result is achieved through:

- perform orbital flight SPACECRAFT in near-circular orbit at the proposed height,

- 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 the required duration natural ohla the Denia radiator-teplocluchenka in the shadow of the planet,

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

Consequently, the proposed action and the proposed terms of their implementation, it is possible to implement shading radiator-teplocluchenka rotating security Council at any time and in any location of the SPACECRAFT at the current stage of the orbit. This fact provides the possibility to reset the heat sink-teploizolyatsii at any desired time, for example, at any desired time, which is specified by the sequence diagram of the execution of the target operations. So, when targeted operations KA activated side apparatus, the elements of which are heated, and this heat is accumulated and discharged into the space through the radiators-emitters. When this sequence diagram accumulation and discharge of heat corresponds to the target sequence diagram of operations of the SPACECRAFT. Thus it is necessary to reset the heat within the required time determined by the realization of the target SPACECRAFT operations. This opportunity is provided by the proposed method.

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-Teplolux the residents, posted on the modules of the ISS Russian segment.

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 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 height of the orbit determines the value of the angle between the direction of the sun and the orbit plane of the spacecraft β^*in which the duration of the shadow part of the loop orbit is equal to the required time duration of the reset heat radiator teploscat the LEM on the circuit, determine the turns of the orbit on which the current value of the angle between the direction of the Sun and the plane of the orbit more videopreteen values of β^*and videopreteen orbits orbits perform rotating solar panels around the 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 when passing spacecraft illuminated side of the coil, and orbiting spacecraft carry out on near-circular orbit with a height not more than
,
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,
P is the orbital period of the spacecraft,
T - the duration of the shadow part of the revolution,
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,
R is the radius of the planet.