An optimized analytical solution for geostationary debris removal using solar sails

Kelly, Patrick; Bevilacqua, Riccardo

doi:10.1016/j.actaastro.2019.05.055

Cited by 21 publications

(11 citation statements)

References 18 publications

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“…Closed‐form expressions for locally optimal sail orientations are known to exist, which produce extremal rates of change for a desired orbital parameter 26 . It has been shown by Kelly and Bevilacqua 32 that the SRP response can be optimized with respect to some primer vector

ζ

. Physically,

ζ

can be defined as the dynamic constraint vector corresponding to the rate of change in a specified orbital parameter such as

ξ

(specific orbital energy), a , or e .…”

Section: Solar Sailingmentioning

confidence: 99%

“…From Kelly and Bevilacqua, 32 locally optimal sail angles are given as

\begin{align} α^{⋆} & = \tan^{prefix- 1} ((), \frac{prefix- 3 \cos γ + \sqrt{\cos^{2} γ + 8}}{4 \sin γ}) \in ([], 0, \frac{π}{2}), \end{align}

\begin{align} β^{⋆} & = 0 . \end{align}

In instances where a specific orbital parameter rate is to be optimized,

ζ

is always defined and

γ

is necessarily uncontrollable as

{\hat{e}}_{⊙}

and

ζ

uniquely define the

false{{\hat{e}}_{1}, {\hat{e}}_{2}, {\hat{e}}_{3} false}

basis. In addition, with

false{α^{⋆}, β^{⋆} false}

defined, the sail system will orient deterministically, achieving locally optimal SRP contributions to maximize the rate of change associated with the given

ζ

.…”

Section: Solar Sailingmentioning

confidence: 99%

“…Maneuvering solutions are obtained by subdividing the spacecraft trajectory into multiple phases, alternating between illuminated and eclipsed states in a similar manner as previous works 3,5 . The proposed maneuvers will support the TugSat concept where a small satellite is tasked with repeatedly deorbiting large orbital debris from the GEO belt using SRP propulsion 31,32 . The TugSat mission involves a deorbit segment and a phasing segment.…”

Section: Introductionmentioning

confidence: 99%

“…The deorbit maneuver was shown achievable in 220 days while the return maneuver would occur anywhere between 180 days to over 10 years. Deorbit times are improved for various sail sizes in Kelly and Bevilacqua, 32 where a closed‐form sail maneuvering strategy is introduced and optimized heuristically using particle swarm optimization, ultimately reducing deorbit times by over 20%. In this work, deorbit times are further improved by steering the direction of the primer vector presented in Kelly and Bevilacqua, 32 and implementing sail orientations based on the closed‐form solution.…”

Section: Introductionmentioning

confidence: 99%

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Geostationary debris mitigation using minimum time solar sail trajectories with eclipse constraints

Kelly

Bevilacqua

2020

Optim Control Appl Methods

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SummaryMinimum time solar sailing trajectories are introduced using a combination of indirect and direct optimal control techniques. Here, large‐scale, multiphase optimal control problems are solved using a pseudospectral collocation technique applied to an orbital debris mitigation concept. These solutions are obtained for realistic sail dimensions, producing multirevolution, Earth‐centered trajectories while accounting for uncontrolled spacecraft dynamics in the eclipse regions. Specifically, minimum time solutions for orbit transfer and phasing maneuvers are obtained using only solar radiation pressure for propulsion and control. First, an optimal primer vector steering history is obtained through numerical approximation. Locally optimal, closed‐form solutions are then implemented based on the primer vector direction, resulting in minimum time satisfaction of desired terminal orbital conditions. In addition, a novel solution strategy is presented for multiphase optimal control problems characterized by uncontrollable dynamics with flexible phase boundaries. The maneuvers presented will be shown to enable efficient orbital debris mitigation for large‐scale debris in geostationary orbits.

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ζ

. Physically,

ζ

can be defined as the dynamic constraint vector corresponding to the rate of change in a specified orbital parameter such as

ξ

(specific orbital energy), a , or e .…”

Section: Solar Sailingmentioning

confidence: 99%

“…From Kelly and Bevilacqua, 32 locally optimal sail angles are given as

\begin{align} α^{⋆} & = \tan^{prefix- 1} ((), \frac{prefix- 3 \cos γ + \sqrt{\cos^{2} γ + 8}}{4 \sin γ}) \in ([], 0, \frac{π}{2}), \end{align}

\begin{align} β^{⋆} & = 0 . \end{align}

In instances where a specific orbital parameter rate is to be optimized,

ζ

is always defined and

γ

is necessarily uncontrollable as

{\hat{e}}_{⊙}

and

ζ

uniquely define the

false{{\hat{e}}_{1}, {\hat{e}}_{2}, {\hat{e}}_{3} false}

basis. In addition, with

false{α^{⋆}, β^{⋆} false}

defined, the sail system will orient deterministically, achieving locally optimal SRP contributions to maximize the rate of change associated with the given

ζ

.…”

Section: Solar Sailingmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Geostationary debris mitigation using minimum time solar sail trajectories with eclipse constraints

Kelly

Bevilacqua

2020

Optim Control Appl Methods

Self Cite

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show abstract

“…A concept for a mission to actively remove orbital debris using a device in a CubeSat form factor was studied by Hakima et al (2018). Kelly and Bevilacqua (2019) studied a solar sail deorbit method, and Underwood et al (2019) proposed the InflateSail satellite for the QB50 plan (a 3.2 kg 3U CubeSat equipped with an inflatable mast and a deployable drag sail).…”

Section: Introductionmentioning

confidence: 99%

Electromagnetic-launch-based method for cost-efficient space debris removal

Hou

Yang

et al. 2020

Open Astronomy

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The increase in space debris orbiting Earth is a critical problem for future space missions. Space debris removal has thus become an area of interest, and significant research progress is being made in this field. However, the exorbitant cost of space debris removal missions is a major concern for commercial space companies. We therefore propose the debris removal using electromagnetic launcher (DREL) system, a ground-based electromagnetic launch system (railgun), for space debris removal missions. The DREL system has three components: a ground-based electromagnetic launcher (GEML), suborbital vehicle (SOV), and mass of micrometer-scale dust (MSD) particles. The average cost of removing a piece of low-earth orbit space debris using DREL was found to be approximately USD 160,000. The DREL method is thus shown to be economical; the total cost to remove more than 2,000 pieces of debris in a cluster was only approximately USD 400 million, compared to the millions of dollars required to remove just one or two pieces of debris using a conventional space debris removal mission. By using DREL, the cost of entering space is negligible, thereby enabling countries to remove their space debris in an affordable manner.

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Survey on research and development of on-orbit active debris removal methods

Zhao

Liu

2020

Sci. China Technol. Sci.

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An optimized analytical solution for geostationary debris removal using solar sails

Cited by 21 publications

References 18 publications

Geostationary debris mitigation using minimum time solar sail trajectories with eclipse constraints

Geostationary debris mitigation using minimum time solar sail trajectories with eclipse constraints

Electromagnetic-launch-based method for cost-efficient space debris removal

Survey on research and development of on-orbit active debris removal methods

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