Deployment analysis of a planar deployable support truss structure

Wang, Dandan; Liu, Rongqiang; Wang, Yan; Guo, Hongwei; Cong, Qian; Zhang, Congfa

doi:10.1109/icma.2013.6618099

Cited by 5 publications

(5 citation statements)

References 10 publications

(3 reference statements)

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“…Figure 8 presents a multi-closed-loop deployable mechanism which is assembled in series by two identical two-loop deployable mechanisms (TLDM) described in Figure 4. 14 This assembly mechanism is composed of 12 rods, 4 closed loops, and capable of 4 DOFs. We call it 2-TLDM in this article.…”

Section: Adjustment Of Two-loop Deployable Mechanism In Multi-configurationsmentioning

confidence: 99%

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Accuracy model, analysis, and adjustment in the context of multi-closed-loop planar deployable mechanisms

Yang

Xie

Zhang

et al. 2016

Advances in Mechanical Engineering

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The links of the multi-closed-loop deployable mechanism are generally adjusted when being assembled, for the purpose of making the whole mechanism satisfy the requirements in fully deployed, folded, or the other key configurations. In order to calculate the appropriate adjustment amount, the complex adjustment amount of the whole mechanism is first defined by root mean square. And then, the adjustment model for planar mechanism involving different constraints is constructed according to the different situations. Through linearization of this model, it can be applied to calculate the adjustment sensitivity of this type of mechanisms. Second, with the factor of the practical adjustment in engineering, the three computation modes of adjustment (bidirectional adjustment, invariant adjustment, and unidirectional adjustment) have been developed. Furthermore, the multi-configuration adjustment approach has been proposed to make the assembled mechanism satisfy the requirements in different configurations. At last, all the above approaches in this article have been implemented in the scissor-like element mechanism and two-loop deployable mechanism. The achievement of this research provides a significant reference for assembling the multi-closed-loop mechanisms.

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Section: Adjustment Of Two-loop Deployable Mechanism In Multi-configurationsmentioning

confidence: 99%

“…Patel and Ananthasuresh 13 developed a kinematic theory for radially foldable closed-loop linkages using the algebraic locus of the coupler curve. Liu and colleagues 14 discussed the deployment planar deployable support truss structure by means of the closed-loop equations and the Kane equation.…”

Section: Introductionmentioning

confidence: 99%

Accuracy model, analysis, and adjustment in the context of multi-closed-loop planar deployable mechanisms

Yang

Xie

Zhang

et al. 2016

Advances in Mechanical Engineering

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“…In equations (13) and (14), the first-and the second-order derivative of Ál e with respect to x, which can be derived from equation 3 Under the small displacement assumption, the second term of equation 14can be ignored. Prior to approaching equation 12, we have to form the gradient vector and the second-derivative matrix by equations (15) and (16). In this situation, Ál e can be regarded as the differences between the nominal length and the unassembled length.…”

Section: Analysis Model Involving Manufacturing Errormentioning

confidence: 99%

“…For solving the kinematics problems, the method of kinematic differentials is often used as an efficient tool. 14,15 Anantharaman and Hiller presented a simple approach to the numerical simulation of these systems. 16 Based on the Jacobian matrices, the different kinds of the singularities encountered in closed-loop chains were identified.…”

Section: Introductionmentioning

confidence: 99%

Accuracy analysis of a multi-closed-loop deployable mechanism

Yang

Luo

Zhang

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part C:

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The multi-closed-loop deployable mechanism generates distortion which is caused by the deviation of each rod after being assembled as a result of manufacturing error, which leads to the degradation of the antenna performance or excess of the given envelope. The multi-closed-loop deployable mechanisms consist of many closed loops and have complicated topology structure and loop constraints coupling. The positioning accuracy analysis of such mechanism is more difficult than the open-chain mechanisms or the single-loop mechanisms. In order to solve this problem, first, based on the minimum of elastic deformation energy, the distortion analysis model is constructed. Second, the sensitivity of the mechanism distortion to the individual rod deviation is investigated by examining the Lagrange multipliers. By means of this model, the allowable tolerance of multi-closed-loop deployable mechanism is discussed and calculated. Last but not least, the above method and model are applied to the four-closed-loop deployable mechanism to solve the problems of its distortion, sensitivity, and tolerance in both fully deployed and folded configurations. It is demonstrated in this paper that the model and method proposed are well accommodated to the accuracy analysis of such mechanisms. The achievement of the research will help reduce the difficulties of the assembling and manufacturing of the multi-closed-loop deployable mechanisms.

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“…Meng et al [10], Bo et al [11] and Siriguleng et al [12] proposed structure design methods of basic units and their constructed regular polygonal prisms to describe the mechanism principles of motor-driven hoop truss antennas. Liu et al [13], Wang et al [14], Guo et al [15,16], Takamatsu et al [17] and Tian et al [18,19] used experimental and numerical methods to design the truss structures, sliding hinges and driving springs of the truss antennas, aiming to ensure their reliable deployment driven by the elastic potential energy. Meanwhile, Li et al [20] and Santoni et al [21] studied the vibration characteristics of spring-deployed solar arrays on a satellite during deployment in orbit and found that the vibration of solar arrays has a larger amplitude and longer decay time under in-orbit vacuum conditions than on the ground.…”

Section: Introductionmentioning

confidence: 99%

Dynamic Behavior of Satellite and Its Solar Arrays Subject to Large-Scale Antenna Deployment Shock

Zhang,

Wu,

Han

et al. 2024

Aerospace

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Satellites should be equipped with more and more deployable, large, flexible appendages to improve their service efficiency and reduce launch costs. The spring-driven deployment method of flexible appendages has been widely applied and generates great instantaneous shock loads on satellites, maybe affecting the safety of other flexible appendages, but the current related investigations for satellites with multiple large flexible appendages are insufficient. In this study, the deployment test of the antenna itself was conducted, and the attitude changes in a satellite during antenna deployment were telemetered. Then, a related dynamical model of the satellite was established and verified by the telemetry values of the satellite. Finally, the shock mechanism transmitted to solar arrays was analyzed, and the effect of solar array attitude was discussed. The results show that the simulated method of antenna deployment equivalent to the shock loads tested was thought to be efficient, though it could cause a small non-zero constant of the simulated angular velocities in the antenna deployment direction. The shock-induced moments, except the rotation direction of the solar array drive assembly (SADA), should be highlighted for the antenna deployment dynamic design of satellites, and the solar array attitude has few effects on the shock-induced loads at the SADA.

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Deployment analysis of a planar deployable support truss structure

Cited by 5 publications

References 10 publications

Accuracy model, analysis, and adjustment in the context of multi-closed-loop planar deployable mechanisms

Accuracy model, analysis, and adjustment in the context of multi-closed-loop planar deployable mechanisms

Accuracy analysis of a multi-closed-loop deployable mechanism

Dynamic Behavior of Satellite and Its Solar Arrays Subject to Large-Scale Antenna Deployment Shock

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