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For the three-axis stabilization of the spacecraft in the orbital coordinate system, including in the indirect equilibrium position, an electrodynamic control method is used based on the simultaneous use of two control torques that affect the dynamics of the spacecraft’s rotational motion in the Earth’s magnetic field (EMF), namely, the Lorentz torque and the torque of magnetic interaction. It is assumed that the spacecraft, equipped with an electric charge with a controlled vector of static moment of charge of the first order and a controlled intrinsic magnetic moment, moves in a Keplerian circular Earth orbit of arbitrary inclination. It was previously shown that combining two control systems, magnetic and Lorentz control, into a single electrodynamic control system (EDCS) makes it possible to successfully solve various problems of controlling the angular motion of spacecraft. Unlike many well-known studies performed for one or another approximate EMF model, this work does not impose restrictions on the accuracy of the EMF approximation. Previous studies have shown the limited capabilities of the EDCS for spacecraft moving in orbits close to the polar ones, due to the presence in this case of such points on the spacecraft trajectory in which it is possible for the lines of action of the geomagnetic induction vector and the spacecraft velocity vector relative to the EMF. Therefore, in this paper, the problem of overcoming these difficulties is posed and solved. A modification of the EDCS is proposed, based, firstly, on optimizing the control of the angular motion of the spacecraft and, secondly, on limiting the maximum value of the modulus of the vector of the center of charge relative to the center of mass of the spacecraft, which must be created during control. A method for selecting parameters for a modified EMF is recommended. The presented results of numerical experiments for spacecraft located in polar and circumpolar orbits not only demonstrate the operability of the proposed modification of the EDCS, but also indicate the possibility of technical implementation of the modified electrodynamic method of three-axis spacecraft stabilization.

Industrial robots have made it possible for robotics to become a worldwide discipline both in economy and in science. However, their capabilities are limited, especially regarding contact tasks where it is required to regulate or at least limit contact forces. At one point, it was noticed that elasticity in the joint transmission, which was treated as a drawback previously, is actually helpful in this regard. This observation led to the introduction of elastic joint robots that are well-suited to contact tasks and cooperative behavior in particular, so they become more and more widespread nowadays. Many researchers try to implement such devices not with trivial series elastic actuators (SEA) but with more sophisticated variable stiffness actuators (VSA) that can regulate their own mechanical stiffness. All elastic actuators demonstrate shock robustness and safe interaction with external objects to some extent, but when stiffness may be varied, it provides additional benefits, e. g., in terms of energy efficiency and task adaptability. Here, we present a novel variable stiffness actuator with a magnetic coupler as an elastic element. Magnetic transmission is contactless and thus advantageous in terms of robustness to misalignment. In addition, the friction model of the transmission becomes less complex. It also has milder stiffness characteristic than typical mechanical nonlinear springs, moreover, the stiffness curve has a maximum after which it descends. Therefore, when this maximum torque is achieved, the coupler slips, and a new pair of poles defines the equilibrium position. As a result, the risk of damage is smaller for this design solution. The design of the joint is thoroughly described, along with its mathematical model. Finally, the control system is also proposed, and simulation tests confirm the design ideas.