Orbit Injection Maneuvers via Indirect Heuristic Method and Variable-Time-Domain Neighboring Optimal Guidance

2016 ◽  
Author(s):  
Mauro Pontani
Keyword(s):  
Time Domain ◽  
Heuristic Method ◽  
Variable Time ◽  
Optimal Guidance ◽  
Neighboring Optimal Guidance

Variable-time-domain neighboring optimal guidance applied to space trajectories

2015 ◽  
Vol 115 ◽  
pp. 102-120 ◽  
Author(s):  
Mauro Pontani ◽  
Giampaolo Cecchetti ◽  
Paolo Teofilatto
Keyword(s):  
Time Domain ◽  
Space Trajectories ◽  
Variable Time ◽  
Optimal Guidance ◽  
Neighboring Optimal Guidance

scholarly journals Neighboring Optimal Guidance and Constrained Attitude Control for Accurate Orbit Injection

2021 ◽  
Author(s):  
Mauro Pontani ◽  
Fabio Celani
Keyword(s):  
Attitude Control ◽  
Initial Position ◽  
Low Earth Orbit ◽  
Guidance And Control ◽  
Optimal Guidance ◽  
Combined Use ◽  
Upper Stage ◽  
Neighboring Optimal Guidance ◽  
And Control ◽  
Guidance Technique

AbstractAccurate orbit injection represents a crucial issue in several mission scenarios, e.g., for spacecraft orbiting the Earth or for payload release from the upper stage of an ascent vehicle. This work considers a new guidance and control architecture based on the combined use of (i) the variable-time-domain neighboring optimal guidance technique (VTD-NOG), and (ii) the constrained proportional-derivative (CPD) algorithm for attitude control. More specifically, VTD-NOG & CPD is applied to two distinct injection maneuvers: (a) Hohmann-like finite-thrust transfer from a low Earth orbit to a geostationary orbit, and (b) orbit injection of the upper stage of a launch vehicle. Nonnominal flight conditions are modeled by assuming errors on the initial position, velocity, attitude, and attitude rate, as well as actuation deviations. Extensive Monte Carlo campaigns prove effectiveness and accuracy of the guidance and control methodology at hand, in the presence of realistic deviations from nominal flight conditions.

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