Efficient inclination control for geostationary satellites

Slavinskas, D. D.; Dabbaghi, H.; Benden, W. J.; Johnson, G.K.

doi:10.2514/3.20356

Cited by 21 publications

(5 citation statements)

References 2 publications

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“…(1) and (2) with P h 1 D c i s \ P i C s i c \ P \ to obtain Eq. (6), and, similarly, with P h 2 D c i c \ P i ¡ s i s \ P \ to obtain Eq. (7).…”

Section: General Analysis Of North -South Drift: Impulsive Maneuvmentioning

confidence: 97%

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Optimal Steering for North-South Stationkeeping of Geostationary Spacecraft

Kechichian

1997

Journal of Guidance, Control, and Dynamics

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The problem of north-south stationkeeping of geostationary spacecraft using electric thrusters is analyzed. Pure yawing with short-duration low-thrust arcs applied infrequently is assumed, and the dynamics are cast in continuous form to obtain an analytic steering law in the inclination-node (i; X ) space that brings the spacecraft back to the ideal initial orbit orientationfor the initiation of a free-drift period that satis es the inclinationconstraint for the longest possible duration. This problem is posed as a minimum-time navigation problem between two i; X pairs and is similar to the Zermelo problem of navigating a ship in strong variable currents. The simple linear steering law thus obtained is easy to use and fuel optimal compared to other suboptimal strategies for travel between two given (i; X ) pairs.

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“…(1) and (2) with P h 1 D c i s \ P i C s i c \ P \ to obtain Eq. (6), and, similarly, with P h 2 D c i c \ P i ¡ s i s \ P \ to obtain Eq. (7).…”

Section: General Analysis Of North -South Drift: Impulsive Maneuvmentioning

confidence: 97%

“…For near-equatorial orbits or small i, c i » D 1 such that the system in Eqs. (6) and (7) can now be cast in the canonical form by way of a quadratic Hamiltonian H in the nonsingular variables h 1 and h 2 , after a change of variable from time t to \ M (Ref. 7).…”

Section: General Analysis Of North -South Drift: Impulsive Maneuvmentioning

confidence: 99%

Optimal Steering for North-South Stationkeeping of Geostationary Spacecraft

Kechichian

1997

Journal of Guidance, Control, and Dynamics

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“…So, the single station orbit determination meets the performance requirement. [8], Maximum Compensation Target (MCT), Track Back Chord Target (TBCT) and two kinds of EWSK strategy such as one-burn and two-burn. In normal operation, we used to apply MFT/one-burn strategy for NSSK/EWSK maneuver to minimize consumed fuel.…”

Section: Figure 1 Coms Satellite Azimuth Bias Estimation By Orbit Dementioning

confidence: 99%

Operational validation of the flight dynamics system for COMS satellite

Lee¹,

Hwang²,

Kim³

et al. 2012

JAESA

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As a multi-mission GEO satellite, COMS has three payloads including Ka-band communications, geostationary ocean color imager, and meteorological imager. COMS flight dynamics system provides the general on-station functions such as orbit determination, orbit prediction, event prediction, station-keeping maneuver planning, station-relocation maneuver planning, and fuel accounting. There are some specific flight dynamics functions to operate the Eurostar 3000 spacecraft bus such as wheel off-loading management, oscillator updating management, and on-station attitude reacquisition management. In this paper, operational validation of the major functions in COMS flight dynamics system is presented for the first six month of operations period.

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“…Station-keeping by using chemical propulsion is a mature technology and has been applied in plenty of missions [4,5], in which the ground-control center generates the control command by measuring the deviation of the satellite. Due to the nature of the chemical propulsion, chemical-propulsion GEO satellites execute station-keeping maneuvers every two weeks conventionally, resulting in a significant decline in the station-keeping accuracy.…”

Section: Introductionmentioning

confidence: 99%

Geostationary Station-Keeping of Electric-Propulsion Satellite Equipped with Robotic Arms

Xu²,

Zhou

et al. 2022

Aerospace

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We propose two approaches based on feedforward control and model-predictive control, respectively, to solve the station-keeping problem of an electric-propulsion geostationary Earth orbit (GEO) satellite, whose thrusters are mounted on two robotic arms on its anti-nadir face. This novel configuration enables a wider range of thrust direction, making it possible to regard the thrust direction as control variables. To solve this control problem, we present the quick feedforward controller (QFFC) and the fuel-optimal model predictive controller (FOMPC). The QFFC is developed based on the analysis of GEO dynamics and the thruster configuration. The FOMPC applies an optimization algorithm to solve the nonlinear model predictive control (NLMPC) problem with the initial value given by the QFFC. Numerical simulations suggest that both controllers could achieve stable station-keeping over multiple objective elements with fewer thrusters and fewer maneuvers. The QFFC has higher control accuracy and lower computational requirements than the FOMPC, whereas the FOMPC could significantly save fuel consumption. The robustness assessment and other discussions of the controllers are also presented.

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Efficient inclination control for geostationary satellites

Cited by 21 publications

References 2 publications

Optimal Steering for North-South Stationkeeping of Geostationary Spacecraft

Optimal Steering for North-South Stationkeeping of Geostationary Spacecraft

Operational validation of the flight dynamics system for COMS satellite

Geostationary Station-Keeping of Electric-Propulsion Satellite Equipped with Robotic Arms

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