Solar Sail Propulsion for Interplanetary Cubesats

Johnson, Les; Cohen, Barbara; McNutt, Leslie; Castillo-Rogez,

doi:10.2514/6.2015-3895

Cited by 5 publications

(4 citation statements)

References 1 publication

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“…The system design went from a single spool for the booms and single round spool for the sail material to a dual mounted boom deployer and racetrack shaped sail spool (see Figure 7). This design accommodated the new 6U volume allocation, additional boom length, and sail storage area [15].…”

Section: Solar Sailmentioning

confidence: 99%

Near-Earth Asteroid Scout Flight Mission

Lockett

Castillo‐Rogez

Johnson

et al. 2020

IEEE Aerosp. Electron. Syst. Mag.

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Section: Solar Sailmentioning

confidence: 99%

Near-Earth Asteroid Scout Flight Mission

Lockett

Castillo‐Rogez

Johnson

et al. 2020

IEEE Aerosp. Electron. Syst. Mag.

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“…Then, highprecision space exploration is achieved by removing the payload away from the microsatellite platform [1][2][3]. A deployable mechanism [4][5][6], such as a coilable mast, is usually used. A coilable mast is a one-dimensional deployable mechanism consisting of three consecutive longerons and a series of transverse battens and diagonal cables.…”

Section: Introductionmentioning

confidence: 99%

An Iterative Determination Method of an Axial Deployment Force of a Lanyard-Deployed Coilable Mast in Local Coil Mode

Liu,

Sun,

Huang

et al. 2024

International Journal of Aerospace Engineering

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The axial deployment force is an indispensable parameter of a lanyard-deployed coilable mast, which reflects its load capacity in practical applications. However, research on the axial deployment force in the literature is very limited, and there are no mature numerical methods to determine this parameter in the design stage of coilable masts. In this paper, a numerical method for determining the axial deployment force of a lanyard-deployed coilable mast in the local coil mode is presented. Through this method, the designer can quickly obtain the estimated value of the axial deployment force in the design stage, which is convenient for the quantitative design of parameters. To verify the correctness of the proposed method, a dynamic simulation of the coilable mast is carried out, and a microgravity test is performed. The comparison results show that the error between the numerical method and the simulation and experimental results is less than 5%, which proves the correctness of the proposed method. In addition, the coilable mast studied in this paper has been verified by an actual microsatellite deployment in orbit.

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“…Solar sails enable a number of advanced space missions that would be difficult to carry out with traditional propulsion systems [7,8,9,10], such as mission to Kuiper Belt objects [11], multi-asteroid rendezvous [12], asteroid de-spin and deflection [13], debris removal from geostationary orbit [14] . A typical reference mission that is often used to quantify the performance of a solar sail-based spacecraft is an orbit-to-orbit (that is, ephemeris-free), interplanetary transfer towards inner planets [15,16,17]. In that case, the transfer is usually studied assuming the spacecraft to be subjected only to the gravitational attraction of the Sun and to the propulsive acceleration provided by the solar sail.…”

Section: Introductionmentioning

confidence: 99%