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Presented proofs and simulated results show the practical application and effective performance of designed guidance law.
Moreover, the stability and robustness of the designed guidance law are analyzed.
Although the designed guidance laws are developed for the constant speed missiles, the simulation results for the time-varying speed missiles are also shown to further confirm the designed guidance laws.
Therefore, the designed guidance law is flexible enough to target different touchdown points on the runway and is capable of dealing with large initial condition errors resulted from the previous flight phase.
The designed guidance law can generate new trajectories on-line without any specific requirement on off-line analysis except for the information on the boundary conditions of the A&L phase and instantaneous states of the RLV.
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The designed guidance-control system performance is verified via computer simulations using a generic endo-atmospheric interceptor model.
The designed guidance-control system performance is verified via computer simulations using miniature hypervelocity kinetic energy endo-atmospheric interceptor planar model.
Also, this approach can be used as a tool to design guidance law parameters.
Besides offering the physical insight into device physics, the model provides the basic designing guidance for the ADMDG MOSFET's.
Besides offering the physical insight into device physics, the model provides the basic designing guidance for the DMSG MOSFETs.
The results may provide useful design guidance for tag cloud designers.
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Justyna Jupowicz-Kozak
CEO of Professional Science Editing for Scientists @ prosciediting.com