High-Fidelity Linearized J Model for Satellite Formation Flight

Schweighart, Samuel A.; Sedwick, Raymond J.

doi:10.2514/2.4986

Cited by 294 publications

(156 citation statements)

References 1 publication

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“…Для описа-ния траекторий спутников удобно пользоваться уравнениями движения, запи-санными в относительных координатах. Общий вид уравнений относительного движения двух спутников достаточно сложен для аналитического рассмотре-ния, поэтому на первом этапе используется простая модель движения, описыва-емая системой уравнений Хилла-Клохесси-Уилтшира [14,15]. Модель описыва-ет относительное движение двух спутников, летящих по близким околокруго-вым орбитам в центральном поле тяготения Земли …”

Section: постановка задачиunclassified

Investigation of Control Algorithm Using Aerodynamic Force for Satellite Formation Flying Three-Dimensional Motion

Ivanov

Кушнирук²

2017

KIAM Prepr.

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Section: постановка задачиunclassified

Investigation of Control Algorithm Using Aerodynamic Force for Satellite Formation Flying Three-Dimensional Motion

Ivanov

Кушнирук²

2017

KIAM Prepr.

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“…The differential drag control logic is used in the first phase of the multi-spacecraft rendezvous maneuvers. The relative dynamics between two generic spacecraft, considering the averaged effect of the J 2 perturbation over one orbit, projected in the LVLH coordinate system with respect to the target spacecraft, is represented by the Schweighart-Sedwick equations (Schweighart et al 2002) …”

Section: Dynamics Model Including J and Control Via Differential Dragmentioning

confidence: 99%

“…l, q and φ are coefficients as defined in Schweighart et al (2002), ω represents the current angular rate of the LVLH frame and c is defined as…”

Section: Dynamics Model Including J and Control Via Differential Dragmentioning

confidence: 99%

Multiple spacecraft rendezvous maneuvers by differential drag and low thrust engines

Bevilacqua

Hall

Romano

2009

Celest Mech Dyn Astr

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A novel two-phase hybrid controller is proposed to optimize propellant consumption during multiple spacecraft rendezvous maneuvers in Low Earth Orbit. This controller exploits generated differentials in aerodynamic drag on each involved chaser spacecraft to effect a propellant-free trajectory near to the target spacecraft during the first phase of the maneuver, and then uses a fuel optimal control strategy via continuous low-thrust engines to effect a precision dock during the second phase. In particular, by varying the imparted aerodynamic drag force on each of the chaser spacecraft, relative differential accelerations are generated between each chaser and the target spacecraft along two of the three translational degrees of freedom. In order to generate this required differential, each chaser spacecraft is assumed to include a system of rotating flat panels. Additionally, each chaser spacecraft is assumed to have continuous low-thrust capability along the three translational degrees of freedom and full-axis attitude control. Sample simulations are presented to support the validity and robustness of the proposed hybrid controller to variations in the atmospheric density along with different spacecraft masses and ballistic coefficients. Furthermore, the proposed hybrid controller is validated against a complete nonlinear orbital model to include relative navigation errors typical of carrier-phase differential GPS (CDGPS). Limitations of the proposed controller appear relative to the target spacecraft's orbit eccentricity and a general characterization of the atmospheric density. Bounds on these variables are included

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“…These conditions can be concisely formulated as follows: the vector of control direction should have non-zero components both in the orbital plane and along the normal to the orbit. To describe the relative motion of formation flying spacecraft, the Schweighart and Sedwick (2002) modification of the Hill-Clohessy-Wiltshire equations was used. In Guerman et al (2014), the ideas from Guerman et al (2012) were completed with a Newton-type method, which allows one to construct an exact trajectory and corresponding control law based on those obtained from the linearized model.…”

Section: Mathematics Of Nanosatellitesmentioning

confidence: 99%