RU96109536A - METHOD FOR MANAGING A SPACECRAFT BY USING REACTIVE EXECUTIVE AUTHORITIES IN SUPPORT OF A PRESENT ORIENTATION - Google Patents

Claims (3)

1. A method of controlling a spacecraft (SC) using reactive executive bodies while maintaining a given orientation, including measuring the orientation parameters of the reference physical basis, measuring the absolute angular velocity of the spacecraft, maintaining the orientation of the spacecraft according to the specified measured values using a system of power gyroscopes, measuring current values the vector of the kinetic moment in the system of power gyroscopes, the determination of the total vector of the kinetic moment, and from it the parameters of the region located of the beginnings of the kinetic moment in the system of power gyroscopes - the time of saturation of the system (tso), determination of the constant and periodic components in the values of the total vector of the accumulated kinetic moment, unloading the system of power gyros using jet engines of orientation from the indicated constant component of the total vector of the accumulated kinetic moment by i-mi pulses, where i = 0, 1, 2, 3, ..., by simultaneously applying unloading torque from jet engines to the spacecraft hull with a minimum orientation duration and equal opposite oppositely directed moment from power gyroscopes, characterized in that at the moment of starting orientation maintenance, they determine the time interval [to, tso], compare it with a given interval of orientation maintenance and, if the specified interval is less than the interval, determine on the indicated interval the direction of the unit vector of the constant component of the predicted values of the total vector of the kinetic moment in the absolute inertial basis is determined in the absolute inertial basis by component for each projection predicted values of the total angular momentum vector of constant slope
component with respect to the longitudinal time axis of maintaining orientation and the boundary of the region of disposable values of the kinetic moment vector in the system of power gyroscopes, determine the component-wise direction of the unit vector of the unloaded kinetic moment in the absolute inertial basis in the direction of the unit constant vector component of the predicted values of the total kinetic moment vector and the slope of the constant component the predicted values of the total vector of kinetic moment by wearing to the longitudinal time axis of maintaining the orientation and the boundary of the domain of the available values of the kinetic momentum vector in the system of power gyroscopes, in this case, if the slope of the component of the specified vector is directed from the time axis to the boundary of the region or parallel to the time axis, then the corresponding component of the unit vector of the unloaded kinetic moment is assigned the corresponding the value of the component of the specified unit vector of the constant component
the total vector of the kinetic moment, and if the slope of the component of the specified vector is directed from the boundary of the region to the time axis, then the corresponding component of the unit vector of the unloaded kinetic moment is assigned a value opposite to the value of the component of the specified unit vector of the constant component of the total vector of the kinetic moment, kinematic parameters are determined on the same segment orientation of the associated basis with respect to the absolute inertial basis for which the consumption of the working ate jet engines of orientation for unloading the system of power gyroscopes from a single vector of unloaded kinetic moment of a certain direction is minimal, and in the process of maintaining orientation from the measured values of the orientation parameters of the reference physical basis and the angular velocity of the spacecraft’s body, the current kinematic parameters of the position of the connected basis relative to the absolute inertial basis are determined, compared current kinematic parameters with
the segments [t1, tsiη] are determined and if they coincide at the time tl of optimal unloading, where tsiη are the times of saturation of the system of power gyroscopes, determined taking into account the initial conditions for the total vector of kinetic moment after the predicted delivery of unloading pulses from jet engines with orientation in η the axes of the associated basis, taking into account the directions determined by the projections of the unit vector of the unloaded kinetic moment,
they are compared with each other and the ηth axis is selected for the largest value of the segment for unloading, and after unloading, the segment [tl, t si] is determined, where t'si is the time of saturation of the system of power gyroscopes, determined taking into account the initial conditions for the total vector kinetic moment obtained at the end of the next i-th discharge, compare a certain segment with the remaining interval of maintaining a given orientation and, if the specified segment is less than the remaining interval, conduct the next i-th discharge, each time eating the ηth unloading axis, until the next segment [tl, t'si] is greater than or equal to the remaining interval, and before each unloading pulse, the condition under which the subsequent predicted segment [tl, ts (i + l), after the next i-th switching on of the jet engines of orientation, there will be more than the previous segment [tl, t'si], if the specified condition is not fulfilled, then unloading is stopped, the last value tsi is fixed and the maintenance of the specified orientation is continued until time t2, where t2 is the optical time instant total unloading on the segment [tl, t'si], then, at time t2, repeat the above cycle of unloading the system of power gyroscopes with the help of jet orientation engines until the moment when the next time interval of waste-free orientation maintenance is greater than or equal to the remaining orientation interval, if if this condition is not fulfilled, then the modes of maintaining orientation are cycled until the next moment of time of optimal unloading and the unloading of power gyroscopes by means of jet orientation engines until niya of this condition.  2. The control method of the spacecraft according to claim 1, characterized in that in the case of several equivalent moments of time of optimal unloading, the first of them is selected in the course of time to maintain a given orientation, and in the remaining ones, the conditions are met against the predicted total values of the kinetic moment vector, in which the segment determining the saturation of the system of power gyroscopes is greater than the remaining interval of maintaining orientation, if the condition is met, continue to maintain the specified orientation, and if not, ny cycle set forth in Claim 1 x i-unloading power gyroscopes using jet orientation.  3. The control method according to claim 1, characterized in that at times of optimal unloading, the value of the unit vector of the unloaded kinetic moment is specified by the values of the total vector of the accumulated kinetic moment on the worked orientation maintenance interval.