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In some cases, the orbital payload mass increases.
From the above equation, the ratio of payload mass to takeoff mass (Mpay/Mo) can be calculated.
The crew makes use of torpor which minimizes launch payload mass.
Introduced criteria of efficiency – payload mass maximization, introduced assumption that engine exhaust velocity is constant.
An iterative method is proposed to directly estimate the payload mass.
Control of a two-link rigid flexible manipulator carrying a moving payload mass is considered.
The controller's robustness against variation of payload mass is improved using parameter-robust linear quadratic Gaussian (PRLQG) method.
The influence of traverse and travel motions, pendulum length and payload mass on the pendulum motion are investigated.
The total available payload mass would be around 34 kg, allowing a wide range of measurement objectives to be addressed.
The results indicate that the peak impact force is not affected by a non-rigidly attached payload mass.
Once the baseline shape is replaced with the optimized shape, it is detected that (1) taking the minimum fuel as an objective function, the take-off mass is 2.07% lighter than the take-off mass of the baseline shape, (2) taking the maximum payload mass as an objective function, the payload mass is 14.3% heavier than the payload mass of the baseline shape.
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CEO of Professional Science Editing for Scientists @ prosciediting.com