Low-Earth-Orbit Constellation Phasing Using Miniaturized Low-Thrust Propulsion Systems

Lafleur, Trevor; Apffel, Nils

doi:10.2514/1.a34905

Cited by 7 publications

(5 citation statements)

References 33 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Since there is no prior knowledge to direct the optimization variables in the relative method, the multivariate complex-constrained single objective optimization problem described by equaltion (12) will be solved the forward order of optimization variable generation-constraint determinationevaluation function calculation. GA is an efficient means to solve multivariate optimization.…”

Section: Relative Phase Maintenance Methodsmentioning

confidence: 99%

“…where the first term describes the deviation of the actual fuel consumption from the expected value, and the second term describes the deviation's variation, 1 w and 2 w are weighting factors. The heterogeneous constellation maintenance problem can be described by equation (12): to optimize the target semi-major axis i t a of each satellite so that the semi-major axis and relative AoL within T satisfy the configuration constraints (determined by equation(3)and equation( 7)), while fuel consumption is optimal(determined by equation( 11)).…”

Section: Maintenance Optimization Modelingmentioning

confidence: 99%

“…Another type of method is to perform orbit control indirectly with the differential drag caused by atmospheric drag or solar pressure. In [7][8][9][10][11][12], the relative position is controlled by adjusting the attitude of the satellite or mechanism. The AeroCub-4 constellation and the 113-satellite-constellation launched by Planet Labs also relied on the differential drag for orbit control.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Optimized relative phase maintenance for heterogeneous area-to-mass ratio microsatellite constellations

Liu

Meng

Jin

2023

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

Long-term maintenance missions present a challenge for low-orbit heterogeneous area-to-mass ratio (AMR) microsatellite constellations due to inconsistent fuel consumption and carrying capacity. Based on the idea of cooperative control, the fuel consumption of fuel-rich satellites is properly increased in this paper to assist fuel-starved satellites in saving fuel, so as to optimize the fuel consumption balance of each satellite and extend the controllable lifetime of the constellation. The evolution of the relative phase under J2 and atmospheric drag perturbation is analyzed. The target configuration and the strategy of maintenance are modeled and optimized based on the principle of fuel consumption balance. The traditional absolute phase maintenance method for heterogeneous AMR constellation is devised. On this basis, the orbit altitude is optimized with the simulated annealing algorithm to improve the fuel consumption balance. Based on the relative phase maintenance method, the maintenance strategy is optimized with the genetic algorithm to further reduce fuel and enhance the fuel consumption balance. Finally, the three methods are contrasted.

show abstract

Section: Relative Phase Maintenance Methodsmentioning

confidence: 99%

Section: Maintenance Optimization Modelingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Optimized relative phase maintenance for heterogeneous area-to-mass ratio microsatellite constellations

Liu

Meng

Jin

2023

J. Phys.: Conf. Ser.

View full text Add to dashboard Cite

show abstract

“…37 with satellite catalogue number 46838). Indirect evidence comes from a comparison of satellite orbital elements calculated from the GPS data with those predicted by numerical simulations using GMAT 36 , and a simplified theoretical model based on low-thrust trajectories around a spherical Earth 48 . The theoretical model uses the GPS mean semi-major axis just before manoeuvre 1A begins as an initial condition (backpropagating for earlier times).…”

Section: Methodsmentioning

confidence: 99%

In-orbit demonstration of an iodine electric propulsion system

Rafalskyi

Martínez

Habl

et al. 2021

Nature

Self Cite

View full text Add to dashboard Cite

Propulsion is a critical subsystem of many spacecraft1–4. For efficient propellant usage, electric propulsion systems based on the electrostatic acceleration of ions formed during electron impact ionization of a gas are particularly attractive5,6. At present, xenon is used almost exclusively as an ionizable propellant for space propulsion2–5. However, xenon is rare, it must be stored under high pressure and commercial production is expensive7–9. Here we demonstrate a propulsion system that uses iodine propellant and we present in-orbit results of this new technology. Diatomic iodine is stored as a solid and sublimated at low temperatures. A plasma is then produced with a radio-frequency inductive antenna, and we show that the ionization efficiency is enhanced compared with xenon. Both atomic and molecular iodine ions are accelerated by high-voltage grids to generate thrust, and a highly collimated beam can be produced with substantial iodine dissociation. The propulsion system has been successfully operated in space onboard a small satellite with manoeuvres confirmed using satellite tracking data. We anticipate that these results will accelerate the adoption of alternative propellants within the space industry and demonstrate the potential of iodine for a wide range of space missions. For example, iodine enables substantial system miniaturization and simplification, which provides small satellites and satellite constellations with new capabilities for deployment, collision avoidance, end-of-life disposal and space exploration10–14.

show abstract

“…properly [14] . The design of the network routing optimization algorithm for the LEO constellation can be completed by the above steps, and the calculation of the network routing is done by evaluating the link state [15] .…”

Section: Cos ( ( ) ( ) ( )) Tl M Ts T Ls T Tc Tmentioning

confidence: 99%

Link state-based routing optimization method for low orbit constellation networks

Su¹,

Shi²,

Zhou³

et al. 2023

International Conference on Intelligent Systems, Communications, and Computer Networks (ISCCN 2023)

View full text Add to dashboard Cite

The current conventional routing optimization methods for low-orbit constellation networks have a large impact on satellite energy consumption, for which a link-state-based routing optimization method for low-orbit constellation networks is proposed. By constructing a state-space excitation function based on node energy and delay requirements, and constraining the function. The analysis of the experimental results shows that the routing strategy can effectively reduce the satellite energy consumption under the proposed optimization method.

show abstract

Low-Earth-Orbit Constellation Phasing Using Miniaturized Low-Thrust Propulsion Systems

Cited by 7 publications

References 33 publications

Optimized relative phase maintenance for heterogeneous area-to-mass ratio microsatellite constellations

Optimized relative phase maintenance for heterogeneous area-to-mass ratio microsatellite constellations

In-orbit demonstration of an iodine electric propulsion system

Link state-based routing optimization method for low orbit constellation networks

Contact Info

Product

Resources

About