Explicit Dipole Trajectory Solution for Electromagnetically Controlled Spacecraft Clusters

Schweighart, Samuel A.; Sedwick, Raymond J.

doi:10.2514/1.46363

Cited by 27 publications

(11 citation statements)

References 3 publications

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“…3 and 4, have not very large spacecraft separation. Coulomb force [3,10] and electromagnetic force [4,5] are feasible in close-proximity formation. The operational range of liquid droplet thrusters [7] can reach 1 km, and the spacecraft separation of photon tether formation [1] can extend to tens of kilometers in principle.…”

Section: Numerical Examplesmentioning

confidence: 99%

“…King and Schaub et al proposed the concept of Coulomb force and studied its application to space mission of satellite formation [2,3]. Miller and Scchweighart et al considered a group of vehicles in orbit, which change or maintain their relative separation and orientation through electromagnetic interaction [4,5]. Other inter-spacecraft forces concepts are flux pinning interaction between a magnet field and a superconductor [6], and liquid droplet thrusters [7].…”

Section: Introductionmentioning

confidence: 99%

“…These complex properties therefore make the NGCRE problem solution quite challenging. Moreover, NGCRE is a common problem faced by many kinds of formation, such as Coulomb formation [3,10], electromagnetic formation [4,5], liquid droplet thrusters [7], and FluxPinned Spacecraft Formation [6].…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

An analytical method for out-of-plane relative equilibrium formation using inter-spacecraft forces

Shi

Chen

2015

Acta Astronautica

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Section: Numerical Examplesmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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An analytical method for out-of-plane relative equilibrium formation using inter-spacecraft forces

Shi

Chen

2015

Acta Astronautica

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“…Most pioneering research works on EMFF were conducted by the MIT Space Systems Lab and the University of Tokyo [1][2][3][4][5][6] . These studies focused on the benefits, challenges, dynamics, magnetic dipole determination and hardware technology associated with experimental results.…”

Section: Introductionmentioning

confidence: 99%

An LMI-based decoupling control for electromagnetic formation flight

Huang

Zhang

et al. 2015

Chinese Journal of Aeronautics

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Electromagnetic formation flight (EMFF) leverages electromagnetic force to control the relative position of satellites. EMFF offers a promising alternative to traditional propellant-based spacecraft flight formation. This novel strategy is very attractive since it does not consume fuel. Due to the highly coupled nonlinearity of electromagnetic force, it is difficult to individually design a controller for one satellite without considering others, which poses challenges to communications. This paper is devoted to decoupling control of EMFF, including regulations, constraints and controller design. A learning-based adaptive sliding mode decoupling controller is analyzed to illustrate the problem of existing results, and input rate saturation is introduced to guarantee the validity of frequency division technique. Through transformation, the imposed input rate saturation is converted to state and input constraints. A linear matrix inequalities (LMI)-based robust optimal control method can then be used and improved to solve the transformed problem. Simulation results are presented to demonstrate the effectiveness of the proposed decoupling control.

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“…Usually formation includes more than two satellites, so a method to calculate control current of coils using control force and relative position is need. When fixed one satellite's magnetic strength, a method to find all solution of other satellites' magnetic strengths was given (Schweighart and Sedwick, 2010). In near-earth orbit, earth magnetic field will bring angular momentum accumulation to electromagnetic satellites, and inaccuracy measurement of earth magnetic intensity has an effect on control results especially on attitude of satellites.…”

Section: Introductionmentioning

confidence: 99%

Gathering the fractionated electromagnetic satellites cluster by simulating fish school

Dong

2012

Aircraft Engineering and Aerospace Technology

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Purpose -Fractionated satellite clusters need coming together and avoiding crashing with limited random initial relative motion conditions. It is not necessary to keep the invariable configuration. The purpose of this paper is to put forward a control law which simulates organism swarm motion. Design/methodology/approach -The motion of satellites follows three rules: coming together, velocity homology and avoiding crash. According to the rules, three control forces should be applied to satellite individuals. The final control force is the sum of three control forces. Electromagnetic dipole strengths calculation is formulated as nonlinear optimization problem. Considering control strengths have to be got in real time, iterative steps of optimization algorithm are fixed. Findings -A control law which simulates organism swarm motion is put forward. The simulation shows the organism swarm motion simulation control law can keep fractionated satellite cluster coming together and avoiding crash. When iterative steps of optimization algorithm is fixed, the error of solve nonlinear equations is acceptable. Originality/value -The control law is robust and easy to realize. When electromagnetic satellite cluster need not keep fixed configuration, it is a choice of control law of relative motion.

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Explicit Dipole Trajectory Solution for Electromagnetically Controlled Spacecraft Clusters

Cited by 27 publications

References 3 publications

An analytical method for out-of-plane relative equilibrium formation using inter-spacecraft forces

An analytical method for out-of-plane relative equilibrium formation using inter-spacecraft forces

An LMI-based decoupling control for electromagnetic formation flight

Gathering the fractionated electromagnetic satellites cluster by simulating fish school

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