RU2014123860A - METHOD FOR UNLOADING POWER GYROSCOPES OF A SPACE VEHICLE WITH CREATED MAGNETIC MOMENT - Google Patents

Abstract

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 in a system of power gyroscopes, measuring the induction vector of the Earth’s magnetic field, determining the result of the interaction of the magnetic moments of the current circuits of the spacecraft with the Earth’s magnetic field, unitary discharge torque vector control signal to the current circuits of the spacecraft, by changing the magnitude and pressure of current flow, to ensure the conditions of unloading power gyroscopes from the accumulated kinetic moment, where, characterized in that previously in q-th diagram-forming circuits, where q = 1,2, ..., Q, in each p-th mode of operation of the phased antenna array, where p = 1,2, ..., P, measure the values of the currents in the power circuits I and the areas of the S circuits, and also determine the directions of the normal circuits of the current circuits, determine the magnetic moments for each current circuit and the magnetic moments for each current circuit determine the value of the magnetically about the moment of the phased antenna array in each r-th mode of operation determine the values of the unit vectors of unloading moments created as a result of the interaction of the magnetic moments of the phased antenna array with the Earth’s magnetic field when, then, when the conditions for unloading power gyroscopes from the accumulated kinetic moment are satisfied, where, the operation modes of the phased antenna are determined lattices for unloading the system of power gyroscopes from the accumulated kinetic moment, determine the projection values of the vector of times

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 $$\overrightarrow{B}$$

, the definition obtained as a result of the interaction of magnetic moments $$\overrightarrow{L}$$

current circuits of a spacecraft with a magnetic field of the Earth, a unit vector of discharge torque $$\overrightarrow{m}$$

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

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

, characterized in that previously in the q-th 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 circuits are measured supply I _pq and areas S _pq contours, and also determine the directions of the normals $${\overrightarrow{n}}_{pq}$$

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

the magnetic moments for each current loop determine the value of the magnetic moment of the phased antenna array in each r-th 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 vector of the unloading moment 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 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 $$\overrightarrow{H}=0$$

.