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In the lateral profile, a novel guidance algorithm is presented.
A novel guidance algorithm for launch vehicle ascent to the desired mission orbit is proposed.
The guidance algorithm targets apogee, perigee, inclination and right ascension of ascending node.
An analysis was completed defining the performance of each guidance algorithm relative to one another within its specific category.
The overall implementation approach is described, together with the guidance algorithm macrologic and structure.
A guidance algorithm for the waypoint constrained atmospheric entry is presented.
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This comprehensive literature survey reviews past and present planetary entry guidance algorithms.
One such challenge is the development of new guidance algorithms that exhibit a higher degree of robustness and flexibility.
Navigation filters perform relative orbit determination based on images of the target spacecraft, and guidance algorithms conduct automated maneuver planning.
Nonlinear modeling of the rocket dynamics, control design as well as guidance algorithms are performed in this paper.
This paper discusses the application of the theory of partially observable Markov decision processes (POMDPs) to the design of guidance algorithms for controlling the motion of unmanned aerial vehicles (UAVs) with onboard sensors to improve tracking of multiple ground targets.
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