Stability of spacecraft’s partially invariant system

Abstract

A method for improving the spacecraft center of mass movement stabilization accuracy in the active phases of trajectory correction is proposed. This method is used during interplanetary and transfer flights, which in some cases provides high navigational accuracy, when rigid trajectory control methods are used. The required stability conditions obtained are consistent with the known criteria in the invariant theory. Computer modeling shows that a partially invariant stabilization system exhibits significant advantages in terms of accuracy when compared to known stabilization systems.

Synthesizing an algorithm to control the angular motion of spacecraft equipped with an aeromagnetic deorbiting system

“…A system of differential equations in osculating elements (1) was chosen for studying the orbital motion of a spacecraft equipped with AMDS. Motion relative to the center of mass of the system consisting of a spacecraft and AMDS is described by Euler dynamic equations (2). These mathematical models of spacecraft dynamics are used for computer modeling of the process of spacecraft stabilization when applying the relevant control law.…”

“…These mathematical models of spacecraft dynamics are used for computer modeling of the process of spacecraft stabilization when applying the relevant control law. For example, feedback linearization (4) was applied to a nonlinear model of the motion of a spacecraft relative to the center of mass (2) in the first stage of synthesis of the law of control of a spacecraft equipped with AMDS. Using this linearization, a modal linear controller (5) to (8) was synthesized.…”

“…Search for effective means of orientation and stabilization control of spacecraft is one of major research challenges in the field of space-rocket hardware. Control system effec-quality of orientation and stabilization [1,2]. Today, gyroscopic devices (flywheels and control moment gyroscopes) used in conjunction with electromagnetic devices serve as the executive devices that provide high-precision stabilization.…”

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“…When the correction speed impulse reaches 30, a reduction in the gross error during the corrective maneuver results in a proportional reduction in the required characteristic velocity during the next correction. Previous reports 2,3 showed an improvement in the accuracy of roll stabilization in the active phase by one order results in a reduction in the total characteristic correction velocity for the Mars HX-1 spacecraft from about 20 to 2m/s, which corresponds to fuel savings of approximately 30 kg or an increase in the payload mass. Due to the relatively low weights of modern scientific instruments (about 3-8), even such a seemingly small increase in the payload weight can significantly extend the research and experimental program of the spacecraft.…”