Guidance and Control Conference

The problem of the integrated guidance and control (IGC) design for strap-down missile with the field-of-view (FOV) constraint is solved by using the integral barrier Lyapunov function (iBLF) and the sliding mode control theory. Firstly, the nonlinear and uncertainty state equation with non-strict feedback form for IGC design is derived by using the strap-down decoupling strategy. Secondly, a novel adaptive finite time disturbance observer is proposed to estimate the uncertainties based on an improved adaptive gain super twisting algorithm. Thirdly, the special time-varying sliding variable is designed and the iBLF is employed to handle the problem of FOV constraint. Theoretical derivation and simulation show that the IGC system is globally uniformly ultimately bounded and the FOV angle constraint is also guaranteed not only during the reaching phase but also during the sliding mode phase.

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Guidance and Control of a Space Robot at Additional Launching and Approaching an Information Geostationary Satellite

2021 28th Saint Petersburg International Conference on Integrated Navigation Systems (ICINS) ◽

10.23919/icins43216.2021.9470829 ◽

2021 ◽

Author(s):

Yevgeny Somov ◽

Sergey Butyrin ◽

Sergey Somov

Keyword(s):

Geostationary Satellite ◽

Space Robot ◽

Guidance And Control ◽

And Control

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Neighboring Optimal Guidance and Constrained Attitude Control for Accurate Orbit Injection

Aerotecnica Missili & Spazio ◽

10.1007/s42496-021-00077-3 ◽

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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