Comparison of Relative Mean Orbital Element Estimation Methods for Spacecraft Formation Flying

Sobiesiak, Ludwik A.; Roth, Niels; Damaren, Christopher J.

doi:10.2514/6.2011-6234

Cited by 3 publications

(3 citation statements)

References 15 publications

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“…In particular, Lee and Park [74] use a measure that is related to the energy required to change states, allowing to compare different configurations through a cost value. The methods developed here will lay out the foundations of using the proposed accurate orbit-attitude coupled model to perform controlled maneuvers, while at the same time helping to save propellant, especially when incorporated into hybrid control methods such as the ones presented by Vatankhahghadim and Damaren [75], Sobiesiak [76], and Sobiesiak and Damaren [77].…”

Section: Equilibria and Stabilizationmentioning

confidence: 99%

“…The results in Table 6.3.1 can be used during the tuning of the controller, as gain values obtained for one configuration may not work properly in a different system set-up. For a scenario where the coupling parameter ε is large (like in the case analysed in this chapter), the attitude can be used as a stand-alone actuator on the orbital trajectory, or together with other types of translational actuation such as low thrust source (Yang et al [68]) in a hybrid controller scheme, similar to the one proposed by Sobiesiak [76], and Sobiesiak and Damaren [77]. The hybrid approach may help to decrease propellant expenditure by exploiting the orbit-attitude coupled dynamics of the small-body, thus extending mission time.…”

Section: 3(c)mentioning

confidence: 99%

“…The effects of the SRP can be used to reinforce the orbit-attitude gravitational coupled force, thus augmenting the actuating force available to control the spacecraft. These effects can be combined with continuous or impulsive thrusting in a hybrid controller such as the one proposed Sobiesiak in [76], and Sobiesiak and Damaren in [77]. Alternatively, the gravity coupling effect can be used to compensate for SRP perturbations, thus nullifying their effects.…”

Section: Combination Of Coupling Effects With Srp In Hybrid Controllersmentioning

confidence: 99%

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Spacecraft Orbit-Attitude Coupled Dynamics in Close Proximity to Small-Bodies

Bolatti¹

2023

Preprint

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This dissertation presents the development of high definition models and techniques that advance the analysis and control of spacecraft dynamics in close proximity to the surface of small-bodies. First, a high definition gravitational field model for asteroids is proposed, that considers the highly irregular shape of the asteroid, while also including a perturbing effect known as gravitational orbit-attitude coupling. This model uses two existing gravitational representations: the polyhedron model to capture the main gravitational terms with high resolution, and a pointmass model that captures the coupling phenomena. The attitude impact on the translational dynamics is then studied under this model, and the possibility of stabilizing the spacecraft about equilibria via the coupling effect is studied. This approach to control is beneficial for reducing propellant consumption during close proximity operations. Next, due to the low magnitude of the orbit-attitude coupling phenomena, an improved method for accurate numerical integration in astrodynamics applications is presented. Since the spacecraft attitude impacts the trajectory, and vice-versa, any change on one aspect of the dynamics during numerical integration will affect the other. Therefore, having an accurate and computationally fast method is paramount to understand long term dynamical behaviour close to asteroids. The proposed methods are based on geometric mechanics principles, are very fast for long term propagations, and allow integration of spacecraft dynamics with high accuracy in highly perturbed gravitational environments. Finally, the inverse problem is studied. This is, knowing the evolution of the spacecraft state vector in time, how can the gravitational field model parameters be obtained. Here, an estimation technique that considers non-homogeneous mass distribution is developed, exploiting the orbit-attitude coupling phenomena. By using the coupling effect as a complement to traditional estimation methods, additional information to estimate density distributions inside the asteroid can be obtained, and an accurate model of the asteroid can be then be constructed. The implications of the results obtained will allow the design of more accurate control laws, and maneuvers required for landing or hovering above the surface can be planned more efficiently, augmenting the capability of future missions to these small-bodies.

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Section: Equilibria and Stabilizationmentioning

confidence: 99%

Section: 3(c)mentioning

confidence: 99%

Section: Combination Of Coupling Effects With Srp In Hybrid Controllersmentioning

confidence: 99%

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Spacecraft Orbit-Attitude Coupled Dynamics in Close Proximity to Small-Bodies

Bolatti¹

2023

Preprint

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Distance-based relative orbital elements determination for formation flying system

Chen

2016

Acta Astronautica

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A Comparison of Algorithms for Computing Differential Mean Orbital Elements in Formation Flying Missions

Wang

Chen

2013

AIAA Guidance, Navigation, and Control (GNC) Conference

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Differential mean orbital elements between the chase and the deputy spacecraft are essential for most control strategies used in spacecraft formation-flying missions. This paper investigates the subject of computing the differential mean orbital elements from the noisepolluted inertial information. The inertial information contains the absolute positions and velocities of the chief spacecraft as well as the relative positions and velocities between the dual spacecraft in the Earth-centered inertial frame. The semianalytical theory of the gravitational perturbed orbit and the mapping from the modified orbital elements to the Cartesian states are respectively introduced. Two representative algorithms, including iterative calculation and extended Kalman filter, are presented in detail. Additionally, a square-root unscented Kalman filter is proposed to overcome the nonlinearity existed in both the semianalytical solutions and the geometry relations between the dual spacecraft. For comparison, Monte Carlo simulations are undertaken to test the accuracy of each algorithm.

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Comparison of Relative Mean Orbital Element Estimation Methods for Spacecraft Formation Flying

Cited by 3 publications

References 15 publications

Spacecraft Orbit-Attitude Coupled Dynamics in Close Proximity to Small-Bodies

Spacecraft Orbit-Attitude Coupled Dynamics in Close Proximity to Small-Bodies

Distance-based relative orbital elements determination for formation flying system

A Comparison of Algorithms for Computing Differential Mean Orbital Elements in Formation Flying Missions

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