scholarly journals Optimal guidance and estimation of a 2D diffusion–advection process by a team of mobile sensors

Automatica ◽  
2022 ◽  
Vol 137 ◽  
pp. 110112
Author(s):  
Sheng Cheng ◽  
Derek A. Paley
Keyword(s):  
Mobile Sensors ◽  
Optimal Guidance

Optimal Guidance LAM Implementation Issues

1988 ◽  
Author(s):  
J. H. Evers ◽  
J. R. Cloutier ◽  
F. Zupancic
Keyword(s):  
Optimal Guidance

Integration of air pollution data collected by mobile sensors and ground-based stations to derive a spatiotemporal air pollution profile of a city

2019 ◽  
Vol 33 (11) ◽  
pp. 2218-2240 ◽  
Author(s):  
Yee Leung ◽  
Yu Zhou ◽  
Ka-Yu Lam ◽  
Tung Fung ◽  
Kwan-Yau Cheung ◽  
...  
Keyword(s):  
Air Pollution ◽  
Mobile Sensors ◽  
Pollution Profile

Assessing Severity of Pulmonary Obstruction from Respiration Phase-Based Wheeze-Sensing Using Mobile Sensors

2020 ◽  
Author(s):  
Soujanya Chatterjee ◽  
Md Mahbubur Rahman ◽  
Tousif Ahmed ◽  
Nazir Saleheen ◽  
Ebrahim Nemati ◽  
...  
Keyword(s):  
Mobile Sensors

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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