RU2001112734A - A method of forming control actions on a spacecraft with power gyroscopes and rotary solar panels - Google Patents

Claims (1)

A method for generating control actions on a spacecraft with power gyroscopes and rotary solar batteries, including measuring a unit direction vector to the Sun

, determination by it and a given increment of the characteristic velocity of the spacecraft

the required control action relative to the direction to the Sun, the control action on the spacecraft and the estimated time of application of the control action on the spacecraft, the formation of the required control action on the spacecraft at the estimated time, characterized in that, starting from the current time, at specified intervals spacecraft absolute angular velocity vector

measure the kinetic moment vector

in the system of power gyroscopes, determine the total vector of the kinetic moment of the spacecraft

, compare the module of the kinetic moment of the spacecraft G with the maximum permissible value of the kinetic momentum G _КР , if G <G _КР , then determine the maximum angle of the normal to the active surface of solar cells relative to the projection onto the orbital plane of the unit direction vector on the Sun α _MAX , at which condition j _PR -j _Н > ΔJ, where J _PR is the supply current from solar panels, j _H is the load current, ΔJ is the maximum permissible value of the difference in the current of supply and consumption, determine the angle of rotation of the normal to active surface of solar cells relative to the projection onto the orbital plane of a unit direction vector on the Sun

at which

for the measured value of the unit direction vector on the Sun, where

is the control force from the influence of the light flux on the surface of solar panels, if | α | <α _MAX , then they form a control action on the spacecraft by rotating the solar panels at an angle α relative to the projection onto the orbit plane of a unit direction vector on the Sun if | α | ≥α _MAX and

then form a control action on the spacecraft by deploying the solar panels at an angle sign (α) α _MAX relative to the projection onto the plane of the orbit of the unit direction vector on the Sun if | α | ≥α _MAX and

then determine

- component of the vector of the total kinetic moment of the spacecraft

in the orbit plane if

, where G _GR is the specified boundary value of the projection of the total kinetic moment of the spacecraft on the orbit plane, exceeding which requires the unloading of the accumulated kinetic moment from the forces of solar pressure, then form a control action on the spacecraft by deploying the solar panels at an angle of sign (α) α _MAX relative to the projection onto the plane of the orbit of the unit direction vector on the Sun, if

, then determine the angle α ₁ = (α _MAX -dα) sign (α), where dα is the set angle of rotation of the solar batteries relative to the maximum value for unloading the accumulated kinetic moment, solar panels are selected, when the angle of α ₁ is turned, the generated control moment

from the forces of solar pressure on the surface of solar cells satisfies the condition

when all other solar batteries are rotated by an angle of sign (α) α _MAX relative to the projection onto the orbit plane of a unit direction vector on the Sun, a control action is formed on the spacecraft by deploying the selected solar batteries at an angle of α ₁ , and all other solar batteries at an angle of sign ( α) α ₂ relative to the projection onto the plane of the orbit of the unit direction vector on the Sun, where α ₂ is the maximum angle of rotation of the remaining solar cells, under which the condition J _PR -j _H > ΔJ is fulfilled.