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\nThis paper introduces a novel robotic assembly concept for ring-like space structures with an internal prestressed cable net, based on the AstroMesh Reflector architecture. The proposed concept uses a stationary robotic assembly facility known as the truss builder. The modular components of the structure are packaged into the truss builder for launch into space and, once in orbit, the truss builder carries out the assembly process by executing simple, repetitive operations. A two-dimensional finite element ABAQUS simulation predicts the kinematics of the assembly sequence of such ring-like structures, capturing physics-based events of the actual assembly process. For six-sided and twelve-sided structures, it is shown that the assembly process can be successfully completed for a range of design parameters of the system.
", "doi": "10.1016/j.euromechsol.2025.105790", "issn": "0997-7538", "publisher": "Elsevier", "publication": "European Journal of Mechanics - A/Solids", "publication_date": "2026-01", "volume": "115", "pages": "105790" }, { "id": "authors:kgt8g-f0691", "collection": "authors", "collection_id": "kgt8g-f0691", "cite_using_url": "https://authors.library.caltech.edu/records/kgt8g-f0691", "type": "article", "title": "Stability of Torsionally Soft, Deployable Structures Supporting Prestressed Membranes", "author": [ { "family_name": "Luo", "given_name": "Wen", "orcid": "0000-0002-7551-5629", "clpid": "Luo-Wen" }, { "family_name": "Pellegrino", "given_name": "Sergio", "orcid": "0000-0001-9373-3278", "clpid": "Pellegrino-S" } ], "abstract": "This paper studies the folding of square, kirigami-inspired space structures consisting of concentrically arranged modular elements formed by thin shells. Localized elastic folds are introduced in the thin shells and different folding strategies can be obtained by varying the location of the folds and the sequence of imposed rotations. Modeling each modular element with rigid rods connected by revolute joints, numerical simulations of the kinematics of folding are obtained, including constraints that represent folding aids and a gravity offload system. These simulations are used to study two specific packaging schemes, and the folding envelopes of a specific structure are analyzed to identify the scheme that is easier to implement in practice. This particular scheme is demonstrated by means of a physical prototype.
\nThis paper introduces the concept of multi-configuration rigidity for kinematically indeterminate structures with elastic springs and unilateral constraints. A simple example is provided by a structure with a single mechanism and a spring that engages two different unilateral constraints. In each of these configurations, the structure can rigidly support loads up to a critical magnitude at which the unilateral constraints become inactive. The general design problem of embedding springs throughout a structure to achieve multi-configuration rigidity, with multiple unilateral constraints and springs, is studied. This problem is cast as a linear program that maximizes the critical loads required to break free from the unilateral constraints, in all target configurations. This problem can be efficiently solved with guarantees of optimality. The formulation is generally applicable to a variety of discrete structures (e.g., linkages, pin-jointed bars, or origami) with unilateral constraints (e.g., contacts or cables).
\nTraditional spacecraft design paradigms rely on stiff bus structures with comparatively flexible appendages. More recent trends, however, trade deployed stiffness for packaging efficiency to stow apertures with larger areas inside existing launch vehicles. By leveraging recent advances in materials and structures, these spacecraft may be up to several orders of magnitude lighter and more flexible than the current state of the art. Motivated by the goal of achieving agility despite structural flexibility, this paper proposes and verifies a quantitative method for determining structure-based performance limits for maneuvering flexible spacecraft. The results demonstrate that, contrary to common assumptions, other constraints impose more restrictive limits on maneuverability than the dynamics of the structure. In particular, it is shown that an attitude control system’s available angular momentum and torque are often significantly more limiting than the compliance of the structure. Consequently, these results suggest that there is an opportunity to design less-conservative, higher-performance space systems that can either be maneuvered faster (assuming suitable actuators are available) or built using lighter-weight, less-stiff architectures that move the structure-based performance limits closer to those of the rest of the system.
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