Solar Sail Halo Orbits at the Sun–Earth Artificial L1 Point

Baoyin, Hexi; McInnes, Colin R.

doi:10.1007/s10569-005-4626-3

Cited by 109 publications

(59 citation statements)

References 16 publications

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“…Therefore, the reflector acceleration cannot exceed 0.245 mm s −2 for the artificial halo orbits found in this work. Similar results are obtained by [Baoyin & McInnes(2006)], [Baig & McInnes(2009)] for halo orbits about artificial L 1 and L 2 points in the Sun-Earth-spacecraft CRTBP using solar sail and low-thrust propulsion, respectively, such that, the reflector normal vector is directed along the Sun-spacecraft line (reflector attitude angle α = 0 • ) or along the Sun-Earth line (reflector attitude vector n = [1 0 0] T ). However, in this paper, both the angle α and vector n are changing about the orbit to satisfy the reflectivity constraint, Eq.…”

Section: Numerical Computation Of Artificial Halo Orbitssupporting

confidence: 78%

“…Analytical and numerical L 2 halo orbits for a solar reflector are obtained using the Lindstedt-Poincaré and differential corrector methods [Thurman & Workfolk (1996)], respectively. Analytical solutions are derived from a third order Taylor series expansion about artificial L 2 point, while the differential corrector method uses as first guess the third order solution ([Szebehely (1967)], [McInnes(1999)], [Baoyin & McInnes(2006)], [Baig & McInnes(2009)], [Salazar et al(2016b)]). The analytical results yield imaginary solutions after the reflector acceleration exceeds 0.245 mm s −2 , i.e.…”

Section: Introductionmentioning

confidence: 99%

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Periodic orbits for space-based reflectors in the circular restricted three-body problem

Salazar

McInnes

Winter

2016

Celest Mech Dyn Astr

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The use of space-based orbital reflectors to increase the total insolation of the Earth has been considered with potential applications in night-side illumination, electric power generation and climate engineering. Previous studies have demonstrated that families of displaced Earth-centered and artificial halo orbits may be generated using continuous propulsion, e.g. solar sails. In this work, a three-body analysis is performed by using the Circular Restricted Three Body Problem (CRTBP), such that, the space mirror attitude reflects sunlight in the direction of Earth's center, increasing the total insolation. Using the Lindstedt-Poincaré and differential corrector method, a family of halo orbits at artificial Sun-Earth L 2 points are found. It is shown that the third order approximation does not yield real solutions after the reflector acceleration exceeds 0.245 mm s −2 , i.e. the analytical expressions for the in-and out-of-plane amplitudes yield imaginary values. Thus, a larger solar reflector acceleration is required to obtain periodic orbits closer to the Earth. Derived using a two-body approach and applying the differential corrector method, a family of displaced periodic orbits close to the Earth are therefore found, with a solar reflector acceleration of 2.686 mm s −2 .

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Section: Numerical Computation Of Artificial Halo Orbitssupporting

confidence: 78%

Section: Introductionmentioning

confidence: 99%

Periodic orbits for space-based reflectors in the circular restricted three-body problem

Salazar

McInnes

Winter

2016

Celest Mech Dyn Astr

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“…16) Baoyin and McInnes 17) used two methods to obtain solar sail halo orbits at the sub L1 point: one to direct the sail normal vector orientated along the Sun-sail line, and the other to orient the sail normal vector along the Sun-Earth line. The two methods generate similar periodic orbits except that they have different requirements for attitude control.…”

Section: Artificial Lagrange Points and Periodic Orbitsmentioning

confidence: 99%

Solar Sail Halo Orbit Control using Reflectivity Control Devices

Gong

2014

Trans. Japan Soc. Aero. S Sci.

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A new solar sail orbit control strategy is proposed for the solar sail halo orbit mission. The reflectivity control device, initially developed for attitude control, is utilized to control the solar sail orbit by switching the states between absorption and specular reflection. The solar radiation pressure force of a solar sail equipped with reflectivity control devices is modeled, and can be changed continuously by adjusting a continuous variable associated with the reflectivity control device. This model is used to study the artificial Lagrange point and periodic orbit around it in the restricted three-body problem. The dynamical equations of motion are linearized around the periodic orbit, and linear quadratic regulator and Floquet theory are utilized to design the control law for the linear time-periodic system. Utilization of attitude adjustment is a way to control the orbit of the solar sail without reflectivity control devices. In this paper, the reflectivity control device is used to stabilize the periodic orbit without attitude adjustment. The results based on attitude adjustment and reflectivity control devices are compared. The simulations indicate that the strategy using reflectivity control devices is more robust with respect to initial errors.

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“…For both cases the time-optimal transfer will be sought for by solving the accompanying optimal control problem with a direct pseudospectral method. Note 3 that, while solar sail displaced LPOs exist (Baoyin and McInnes, 2006), this work only considers the transfer between LPOs in the classical CR3BP. The solar sail acceleration is thus only employed to leave the initial Halo orbit and to transfer towards and wind onto the target Halo orbit.…”

Section: Introductionmentioning

confidence: 99%

Optimal solar sail transfers between Halo orbits of different Sun-planet systems

Heiligers¹,

Mingotti²,

McInnes³

2015

Advances in Space Research

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This paper investigates time-optimal solar sail trajectories between Libration Point Orbits (LPOs) of different circular restricted Sun-planet three-body systems. Key in the investigations is the search for transfers that require little steering effort to enable the transfers with low-control authority solar sail-like devices such as SpaceChips. Two transfers are considered: 1) from a Sun-Earth L 2 -Halo orbit to a Sun-Mars L 1 -Halo orbit and 2) from a Sun-Earth L 1 -Halo orbit to a Sun-Mercury L 2 -Halo orbit. The optimal control problem to find these time-optimal transfers is derived, including a constraint to mimic limited steering capabilities, and is solved with a direct pseudospectral method for which novel first guess solutions are developed. For a near-term sail performance comparable to that of NASA's Sunjammer sail, the results show transfers that indeed require very little steering effort: the sail acceleration vector can be bounded to a cone around the Sun-sail line with a half-angle of 7.5 deg. These transfers can serve a range of novel solar sail applications covering the entire spectrum of sail length-scales: micro-sized SpaceChips could establish a continuous Earth-Mars communication link, a traditional-sized sail provides opportunities for in-situ observations of Mercury and a future kilometer-sized sail could create an Earth-Mars cargo transport gateway for human exploration of Mars.

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Solar Sail Halo Orbits at the Sun–Earth Artificial L1 Point

Cited by 109 publications

References 16 publications

Periodic orbits for space-based reflectors in the circular restricted three-body problem

Periodic orbits for space-based reflectors in the circular restricted three-body problem

Solar Sail Halo Orbit Control using Reflectivity Control Devices

Optimal solar sail transfers between Halo orbits of different Sun-planet systems

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