Study on the criterion to determine the bottom deployment modes of a coilable mast

Ma, Hang; Jian, Han; Zhang, Wei; Wang, Xinsheng

doi:10.1016/j.actaastro.2017.09.035

Cited by 8 publications

(1 citation statement)

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“…To simplify the calculation, a reasonable assumption is made on the longeron deformation in transition zone based on the results of simulations and tests. It is considered that the helical angle of the longeron in segment 1 is maintained as θ deploy = 0 °, and the helical angle of the longeron in segments 2-4 presents a linear change relationship, which is expressed by Equation ( 6) [13]. The purpose of this assumption is only to estimate the initial integral values θ 4 0 and dθ 4 /ds s=0 of segment 4 to make the deformation equation solvable, and it will not affect the solution of the nonlinear state regions of the helical angle.…”

Section: Equations Of the Longeron Deformationmentioning

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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Section: Equations Of the Longeron Deformationmentioning

confidence: 99%