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This paper considers orbit and attitude control methods that use a superconducting coil, which interacts with on-orbit space plasmas and creates a propulsion force.
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An additional attractive feature of the attitude control method is that the structure of the controller is independent of the elastic mode dynamics of the spacecraft, since in practice the measurement of flexible modes is not easy or feasible.
In addition, the prototype kept the balance during the demonstration based on the attitude control method.
One commonly used attitude control method relies on small rocket thrusters.
The effectiveness of the constrained attitude control method is demonstrated through numerical simulation.
Numerical simulation results obtained for the underactuated spacecraft merely indicate effectiveness of the proposed attitude control method.
An optimal attitude control method based upon linear quadratic regulator is applied to a spacecraft in an inclined orbit, alternatively using magnetic torquers and reaction wheels.
Numerical simulation results for a detumbling of a desired orientation maneuver are presented to illustrate the capability of the proposed attitude control method.
This paper presents a nonlinear H∞ state feedback attitude control design method for spacecraft large angle maneuvers, which is subject to moment-of-inertia (MOI) uncertainty.
As compared to traditional low-thrust liquid fuel rocket engines attitude control this method gives an opportunity to increase favorable conditions period in running gravity-sensitive technological processes on board the laboratory.
This paper presents an additive-state-decomposition-based attitude tracking control method for a class of bank-to-turn aerial vehicles subject to unknown disturbances and nonlinear coupling.
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