The Magnetic Attitude Control System for the Parkinson Satellite (PSAT) A US Naval Academy Designed CubeSat

Thienel, Julie; Bruninga, Robert; Stevens, Robert E.; Ridge, Cory; Healy, Chad

doi:10.2514/6.2009-5947

Cited by 4 publications

(8 citation statements)

References 1 publication

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Upon reaching the desired spin rate, the satellite will enter the ¦ne Sun pointing (FSP) mode and point its solar panels towards the Sun using a nonlinear control with only the MTQ and LoS and angular rates information. The control is described in [1,4]. The MGM, the Sun sensors, the MTQ, and the gyros will be used.…”

Section: Attitude Modes and Hardwarementioning

confidence: 99%

“…As a result, the satellite acquires a slow rotational motion at a rate that is equal to twice its orbital motion rate. The Bdot law is further modi¦ed in order to produce a spin motion around a preferred body-axis [1,4,5]. The rationale for creating an additional spin motion stems from the resulting ¤gyroscopic rigidity¥ around the spin axis.…”

Section: Introductionmentioning

confidence: 99%

“…It helps keeping a body axis along a preferred inertial axis, such as the LoS to the Sun along low Earth orbits (LEO) during eclipses, when the Sun sensors are not operational. The precession of the spin axis towards the Sun LoS can be achieved using Sun vector measurements and its time derivative in conjunction with the Earth magnetic ¦eld measurements [4].…”

Section: Introductionmentioning

confidence: 99%

“…As a result, the satellite is able to point towards the Sun with its two other principal axes in an unde¦ned position. Following [4], three other modes are designed for the purpose of demonstration. A modi¦cation of the Sun coarse acquisition law is proposed here, which alleviates the strong nonlinearity due to the absolute value.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Attitude control system of the Delfi-n3Xt satellite

Reijneveld

Choukroun

2013

Progress in Flight Dynamics, Guidance, Navigation, Control, Fault Detection, and Avionics

View full text Add to dashboard Cite

Section: Attitude Modes and Hardwarementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Attitude control system of the Delfi-n3Xt satellite

Reijneveld

Choukroun

2013

Progress in Flight Dynamics, Guidance, Navigation, Control, Fault Detection, and Avionics

View full text Add to dashboard Cite

“…Initial attitude acquisition was demonstrated using magnetorquers 26 . In addition, time-optimal control 27 , neural network control 28 , and H ∞ control 29 techniques were also used along with some other work [30][31][32] in controlling spacecraft attitude using only magnetorquers.…”

Section: Introductionmentioning

confidence: 99%

Magnetorquers only Attitude Maintaining Using Dynamic Attitude Simulator Environment

Gulmammadov

Kahraman

Yavuzyilmaz

et al. 2010

AIAA Modeling and Simulation Technologies Conference

View full text Add to dashboard Cite

Magnetic controllers for maintaining and varying spacecraft's directivity using only magnetorquers are presented using dynamic attitude simulator environment (DASE), which includes a flight computer and the complete satellite communications architecture. Magnetorquers are environmental actuators that on the contrary to reaction wheels do not have any moving parts. For that reason using only magnetorquers for the tasks where precise attitude control is not required prolongs mission lifetime. Despite the inability to produce torque along the Earth's magnetic field vector magnetorquers can still provide the sufficient pointing accuracy for the on-board antennae with help of B-max and VBC controllers. The controllers are designed for RASAT, an Earth observation satellite, to be launched to a sun-synchronous low Earth orbit (LEO) orbit. The satellite ground communication is achieved via rigidly mounted X-band and S-band antennae with restricted radiation patterns. The controllers' purpose is to maximize the high speed communication duration by directing the satellite's side where the antennae are located towards the ground station during each pass. The results show that magnetic actuation provides sufficient pointing accuracy that surpasses the Nadir-pointing flight mode in terms of communication duration. Nomenclature e = error received by a controller SET v = set-point vector B = Earth' magnetic field vector as measured in satellite's body frame m = magnetic dipole moment vector expressed in satellite's body frame  τ = torque vector Z = satellite's +Z vector expressed in orbit frame P K = proportional gain of a controller D K = differential gain of a controller b o R = rotation matrix from orbit frame to body frame / b bi ω  = angular velocity vector of satellite body frame with respect to inertial frame, represented in satellite body frame. I = Inertia matrix of the satellite D T  = total disturbance torques MT T  = torques generated by the magnetorquers 1 Researcher, Electrical and Electronics Engineer, M.Sc.

show abstract