Fast Slew Maneuvers for the High-Torque-Wheels BIROS Satellite

B., Paul Acquatella

doi:10.2322/tjsass.61.79

Cited by 4 publications

(6 citation statements)

References 20 publications

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“…In this paper a sampled-data form of the recently reformulated incremental nonlinear dynamic inversion (INDI) is proposed and applied in the context of spacecraft attitude control. The objective was to bridge the gap between highly sampled INDI formulations (100 -1000 Hz) and their lowly sampled counterparts in the context of spacecraft attitude control where low sampling rates are common (1)(2)(3)(4)(5)(6)(7)(8)(9)(10) . This was done by introducing a sampled-data reformulation of INDI that allows explicit consideration of the sampling time via an approximate sampled-data model in normal form available in the literature.…”

Section: Discussionmentioning

confidence: 99%

“…In this section we describe the nonlinear rotational dynamics model for spacecraft including a generic set of reaction wheels in arbitrary configuration which are driven by exogenous inputs provided by each wheel's powertrain [10,20]. In this paper we make use of the Modified Rodrigues Parameters (MRPs) [66][67][68] as they represent a well defined attitude parameterization for all Eigen-axis rotations in the large domain of 0 • ≤ < 360 • , where is the principle angle rotation around the Euler-axis .…”

Section: Spacecraft Modelmentioning

confidence: 99%

“…Moreover, BIROS' On-Board-Computer (OBC) can only accomodate rotational acceleration or torque commands up to twice per second (2 Hz) which means that these commands must be piece-wise constant sampled-time control inputs. In [10], the problem of designing fast slew maneuvers was considered as a trajectory optimization problem. However, these optimized slews are hardly implementable in practice, even less when agility is required on demand.…”

Section: Attitude Control Simulationsmentioning

confidence: 99%

“…F small satellite systems are expected to be more performant not only for fine pointing capabilities in data acquisition but also in terms of high agility for maneuverability, e. g., for high dynamic slewing capability to command the platform for fast and flexible data acquisition [1][2][3][4][5][6][7][8][9]. This emerging field of 'agile Earth Observation' motivated the development of a high-agility attitude control system [10] for the the satellite platform BIROS (Bispectral InfraRed Optical System) [3] while actuated with a redundant array of three orthogonal 'High-Torque-Wheels' (HTW) [1,2]. However, for agile reorientation, a challenge arises from the fact that time-optimal slew maneuvers are, in general, not of the Euler-axis rotation [11,12] type; especially whenever the actuators are constrained independently [13].…”

Section: Introductionmentioning

confidence: 99%

“…In this paper, we are motivated to find an agile attitude control solution in closed-loop feedback form. This is challenging because of the many nonlinearities involved in reorientation of small satellites as shown in [10,20] which calls for a robust nonlinear control approach.…”

Section: Introductionmentioning

confidence: 99%

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A Sampled-Data Form of Incremental Nonlinear Dynamic Inversion for Spacecraft Attitude Control

Acquatella

Kampen

Chu

2022

AIAA SCITECH 2022 Forum

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This paper presents a sampled-data form of the recently reformulated incremental nonlinear dynamic inversion (INDI) applied for robust spacecraft attitude control. INDI is a combined model-and sensor-based approach mostly applied for attitude control that only requires an accurate control effectiveness model and measurements of the state and some of its derivatives. This results in a reduced dependency on exact knowledge of system dynamics which is known as a major disadvantage of model-based nonlinear dynamic inversion controllers. However, most of the INDI derivations proposed in the literature assume a very high sampling rate of the system and its controller while also not explicitly considering the available sampling time of the digital control computer. Neglecting the sampling time and its effect in the controller derivations can lead to stability and performance issues of the resulting closed-loop nonlinear system. Therefore, our objective is to bridge this gap between continuous-time, highly sampled INDI formulations and their discrete, lowly sampled counterparts in the context of spacecraft attitude control where low sampling rates are common. Our sampled-data reformulation allows explicit consideration of the sampling time via an approximate sampled-data model in normal form widely known in the literature. The resulting sampled-data INDI control is still robust up to a certain sampling time since it remains only sensitive to parametric uncertainties. Simulation experiments for this particular problem demonstrate the bridge considered between INDI formulations which allows for low sampling control rates.

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