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A final small firing of the space shuttle's Orbital Maneuvering System engines, which use hypergolic propellant (fuel that ignites when it comes into contact with its oxidizer), places the orbiter into the desired orbit.
Our objective is to learn the unknown underactuated system dynamics while tracking to a desired orbit and design the control law to achieve stabilization.
The numerical result shows that the tossing design is able to transport payload into desired orbit, and the control law could meet mission requirement.
Analytical results show that the states of the weighted dynamical network can globally asymptotically synchronize onto a desired orbit under the designed controllers.
For synchronizing a colored network onto a desired orbit with respect to the given matrices, open-plus-closed-loop controllers are designed.
At an altitude of 190 miles, the upper stage would then ignite its solid-rocket boosters to propel the spacecraft, carrying the small 219-pound satellite to its desired orbit.
Similar(47)
In this paper, trajectories are designed that use either V∞ leveraging or low thrust to establish cycler vehicles in their desired orbits.
Furthermore, many real complex networks cannot synchronize themselves or synchronize with the desired orbits.
Aerobraking has previously been used to reduce the propellant required to deliver an orbiter to its desired final orbit.
The transfer towards a libration point orbit requires in many cases an immediate injection, meaning the launch system accelerates the spacecraft into its desired transfer orbit.
A novel guidance algorithm for launch vehicle ascent to the desired mission orbit is proposed.
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Justyna Jupowicz-Kozak
CEO of Professional Science Editing for Scientists @ prosciediting.com