Design, fabrication, and evaluation of a passive deployment mechanism for deployable space telescope

Choi, Junwoo; Lee, Dongkyu; Hwang, Kukha; Kim, Byung Kyu

doi:10.1177/1687814019852258

Cited by 12 publications

(4 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In the space exploration project of the United States, the space-folding mechanism is widely used in the development and construction of satellites, space stations, and probes (Ma et al, 2018;Liu et al, 2018;Hu et al, 2022). With the requirement of satellite miniaturization, Choi proposed a high-precision extension arm design scheme (Arita et al, 2018;Choi et al, 2019), which is mainly used for space optical telescopes. The extension arm was based on a quadrangular column and was equipped with an upper panel and a lower panel, a connecting rod, and a supporting module.…”

Section: Introductionmentioning

confidence: 99%

Dynamic analysis of a box-structured satellite deployment mechanism with self-actuated torsion joints

Sheng,

Ma,

2024

Mech. Sci.

View full text Add to dashboard Cite

Abstract. This paper designed a kind of satellite deployment mechanism with a boxed structure and passive torsion joints. This deployment mechanism has significant strengths, including a high base frequency and stiffness, a high ratio of deployed and folded space occupation ratios, and self-actuated joints without needing any external power to drive. In order to analyze the dynamic characteristics of this mechanism, a simplified governing equation is proposed and dynamic behavior is studied systematically, including impact response, harmonic response, and modal analysis. Through systematic research, several conclusions are drawn. Firstly, when the deployment mechanism reached the ending stage of unfolding driven by passive torsional joints, the load base installed on top of the deployment mechanism generated a first-order sharp reaction force and multiple low-order shocks followed, and the system entered a stable state after a certain time of vibration. Secondly, the system can generate a high vibration magnitude at low-frequency excitation when the mechanism is in a fully deployed state and at high-frequency excitation when the mechanism is in a folded state. Thirdly, the first sixth-order natural frequency and vibration shape with different wall thicknesses are obtained by modal analysis. The result shows that only with a 2.5 mm wall thickness can the connecting rod satisfy the design requirement. Through dynamic behavior research, the structure characteristics are obtained which can be used for structure optimization and to provide an effective solution for the design of a box-structured satellite-unfolding mechanism with self-actuated torsion joints.

show abstract

Section: Introductionmentioning

confidence: 99%

Dynamic analysis of a box-structured satellite deployment mechanism with self-actuated torsion joints

Sheng,

Ma,

2024

Mech. Sci.

View full text Add to dashboard Cite

show abstract

“…Wang et al have analyzed the effect of panel misalignment in three degreesof-freedom (DOFs) on radiation patterns in segmented mirror antennas to develop a tolerance budget [15]. Segmented mirror arrays, however, are heavy, bulky, and require a large number of actuators, which can result in high costs required to place them in orbit [16]. Selecting a telescope design based on a deployable origami array instead of a segmented mirror array could offer many benefits, such as shrinking rocket fairing sizes, increasing aperture sizes, decreasing the number of actuators, and decreasing the cost of launches, which could help to increase the frequency of optical telescope missions [16,17].…”

Section: Introductionmentioning

confidence: 99%

“…Segmented mirror arrays, however, are heavy, bulky, and require a large number of actuators, which can result in high costs required to place them in orbit [16]. Selecting a telescope design based on a deployable origami array instead of a segmented mirror array could offer many benefits, such as shrinking rocket fairing sizes, increasing aperture sizes, decreasing the number of actuators, and decreasing the cost of launches, which could help to increase the frequency of optical telescope missions [16,17]. Such an increase could lead to higherresolution images and more space exploration.…”

Section: Introductionmentioning

confidence: 99%

Effects of Panel Misalignment in a Deployable Origami-Based Optical Array

Roubicek

Gao

et al. 2023

ASME Open Journal of Engineering

View full text Add to dashboard Cite

Deployable origami-based arrays can offer many benefits for a wide variety of engineering applications. However, alignment in the deployed state is a primary challenge of these arrays; in optical systems, local (single panel) and global (entire array) misalignment can drastically reduce performance. The objective of this work is to compare the relative sensitivities of different degrees-of-freedom (DOFs) of misalignment in deployable origami-based optical arrays and specify which have the greatest effect on performance. To accomplish this, we suggest a practice for defining local and global misalignment in deployable origami-based arrays, we simulate misalignment perturbations and record the resulting power output, and we use compensation techniques to restore as much lost power as possible. We use a deployable LiDAR telescope based on the hexagonal twist origami pattern as a case study, though the conclusions could be extended to other origami-based systems. From simulation, we find that the DOFs which are the most sensitive to misalignment and for which compensation is not effective are the local decenter X (467% power loss per mm misalignment), local decenter Y (463% power loss per mm misalignment), local tilt (357% power loss per degree misalignment), and local tip (265% power loss per degree misalignment) misalignments. These results could help minimize the need for compensation or position sensing and help optical systems designers to know which DOFs should be carefully controlled to maximize energy output.

show abstract

“…Arita et al (2018) proposed a new deployable structure and analyzed the structural properties by eigen mode analysis. Choi et al (2019) studied the deployment mechanism and designed the customized modules and an assembly fixture to improve the precision and feasibility. Xue et al (2018) studied the influence parameters of the first mode and applied ANSYS analysis to overcome the influence of the long arm length and improve the position accuracy and assembly accuracy.…”

Section: Introductionmentioning

confidence: 99%

Research on assembly accuracy of deployable arm based on Jacobian-Torsor model

et al. 2023

RIA

View full text Add to dashboard Cite

Purpose The purpose of this study is to establish an assembly accuracy analysis model of deployable arms based on Jacobian–Torsor theory to improve the assembly accuracy. Spacecraft deployable arm is one of the core components of spacecraft. Reducing the errors in assembly process is the main method to improve the assembly accuracy of spacecraft deployable arms. Design/methodology/approach First, the influence of composite connecting rod, root joint and arm joint on assembly accuracy in the tandem assembly process is analyzed to propose the assembly accuracy analysis model. Second, a non-tandem assembly process of “two joints fixed-composite rod installed-flange gasket compensated” is proposed and analyzed to improve the assembly accuracy of deployable arms. Finally, the feasibility of non-tandem assembly process strategy is verified by assembly experiment. Findings The experiential results show that the assembly errors are reduced compared with the tandem assembly process. The errors on axes x, y and z directions decreased from 14.1009 mm, 14.2424 mm and 0.8414 mm to 0.922 mm, 0.671 mm and 0.2393 mm, respectively. The errors round axes x and y directions also decreased from 0.0050° and 0.0053° to 0.00292° and 0.00251°, respectively. Originality/value This paper presents an assembly accuracy analysis model of deployable arms and applies the model to calculate assembly errors in tandem assembly process. In addition, a non-tandem assembly process is proposed based on the model. The experimental results show that the non-tandem assembly process can improve the assembly accuracy of deployable arms.

show abstract

Design, fabrication, and evaluation of a passive deployment mechanism for deployable space telescope

Cited by 12 publications

References 16 publications

Dynamic analysis of a box-structured satellite deployment mechanism with self-actuated torsion joints

Dynamic analysis of a box-structured satellite deployment mechanism with self-actuated torsion joints

Effects of Panel Misalignment in a Deployable Origami-Based Optical Array

Research on assembly accuracy of deployable arm based on Jacobian-Torsor model

Contact Info

Product

Resources

About