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The potential concepts are screened for compatibility and are then sized for desired mission using Tsiolkovsky ideal velocity rocket equation.
If the MMET captures the payloads at the ideal velocity, the MMET's orbit and motion state are unchanged.
The curve is interpolated from only 10 samples, which presents three local minimums, and the estimate of 18.3 is close to the ideal velocity.
The velocity feedback loops are formed by collocated ideal velocity sensor and point force actuator pairs, which are unconditionally stable and produce 'sky-hook' damping on the plate.
The Tsiolkovsky ideal velocity rocket equation supported by mass and propulsion modeling is found to be fast and efficient and is applied for sizing and performance modeling of space launch vehicle at the conceptual design phase.
As can be seen from Fig. 10, none of the velocity distributions follow the ideal velocity profile with the velocity gradually decreasing from the center to the perimeter of the plane, and the same is true for the contour maps not displayed in this paper.
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The ideal velocities of payloads with same mass for capture are analyzed, and a mathematical model of capture is proposed.
This partially compensated for the response latency, allowing the eyes to "catch up" with the head and reach their ideal velocities more quickly.
The problem of non-ideal velocity readings is also considered, and the observer is augmented to compensate for bias in the angular and linear velocity measurements.
Ideal eye velocity is defined as the eye velocity that would keep the fovea on the target.
Detonation velocities in rate-sticks with radii close to the failure radius, can be as low as one third of the ideal detonation velocity, which poses a significant challenge for their accurate predictive computational modelling.
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