11 results about "Deployable structure" patented technology

This invention belongs to the field of aerospace composite material manufacturing technology, specifically relating to a method and equipment for forming thermoplastic composite strain energy rods. First, prepreg is laid up to form a preform, which is then pressed by a flatbed pre-pressing device to form a preform sheet intermediate. Subsequently, the preform intermediate is fed into a hot-pressing module with a central heating and two-end cooling gradient temperature field. It undergoes melting and molding in a high-temperature zone and controlled cooling in a low-temperature zone to achieve final shaping. Finally, the formed rod is cooled and shaped, then pulled out at a uniform speed by a traction device and coiled and collected by a winding device, achieving continuous production. The hot-pressing module of the supporting hot-pressing equipment is equipped with a zoned heating and integrated cooling system, which can precisely construct a gradient temperature field and control the cooling rate. This invention, by using gradient temperature control to precisely regulate the material's crystallization behavior and release internal stress, effectively ensures the straightness, dimensional stability, and consistent deployment performance of the strain energy rod, perfectly meeting the manufacturing requirements of strain energy rods for large deployable structures in spacecraft.

This invention relates to an auxiliary folding device for a push-plate type flexible deployable structure, comprising an upper push-plate assembly, a lower push-plate assembly, and a straightening and limiting assembly. The upper push-plate assembly is located on the upper center of the lower box plate of the flexible deployable structure, and the lower push-plate assembly is located on the lower center of the lower box plate. The straightening and limiting assembly is located on both sides of the upper side of the lower box plate, on either side of the upper push-plate assembly. The lower push-plate is used to lift the solar panel in the folding direction, the upper push-plate is used to store the folded solar panel, and the straightening and limiting assembly is used to ensure the straightening and limiting of the solar panel during the folding process, preventing overall deformation or misalignment of the solar panel that would hinder its folding. This invention provides an efficient, convenient, versatile, and environmentally friendly auxiliary folding and retraction device for flexible deployable structures, solving the technical bottlenecks and operational risks of low efficiency and insufficient safety in existing flexible deployable structure folding technologies.

A simulation device for microgravity deployment experiments on the ground is mainly composed of an adjustable leveling structure assembly, an adjustable anti-creep rope assembly, a magnetic levitation de-rotation structure assembly, an adjustable counterweight assembly, and a safety protection rope lock. This device significantly reduces resistance during operation and improves redundancy safety and reliability during microgravity deployment experiments. The invention features simple structure, low rotational resistance, high suspension compensation accuracy, strong versatility and design flexibility, high redundancy safety protection, and good scalability, making it suitable for deployment experiments of large-scale space deployable structures such as space deployable antennas and flexible deployable cabins.

This invention relates to the field of space deployable structure technology, and more particularly to a deployable light-shielding structure based on shape memory materials and its shaping and deployment method. The structure comprises an outer frame and an inner light-shielding cover. The outer frame consists of a top frame, a bottom frame, and multiple shape memory L-shaped beams connecting the two, forming a frustum-shaped boundary after unfolding. The number of inner light-shielding covers matches the sides of the frame; each includes a fan-shaped shape memory skeleton with concentric annular curved lines and a light-shielding cloth. The skeleton can be folded along the curved lines into a radially corrugated laminated ring shell to achieve ultra-high axial compression, and after heating, it can be deterministically unfolded into a planar fan-shaped ring to fill the boundary. This invention adopts a two-stage unfolding method of "boundary first, then filling." This structure integrates the geometric determinism, high folding-to-unfold ratio, and high energy storage characteristics of curved origami with the active controllability of shape memory materials, possessing advantages such as lightweight, high reliability, high precision, smooth and impact-free unfolding, and customizable structure.

The application discloses a winding rib type electrostatic forming film reflecting surface antenna device, which comprises a center wheel cylinder, the center wheel cylinder is a prism, and a plurality of elastic winding ribs are fixedly connected to the side surface of the center wheel cylinder; a flexible cable is arranged between two adjacent elastic winding ribs; a base cable net electrode is laid above the elastic winding rib and the flexible cable; the base cable net electrode is composed of triangular meshes; a film reflecting surface is arranged above the base cable net electrode; the film reflecting surface is in a parabolic shape; the base cable net electrode and the film reflecting surface are connected with an electrostatic power supply through a cable; and the film reflecting surface is connected with the center wheel cylinder. The application adopts an elastic winding rib type deployable structure as a support structure of the whole antenna system. The winding rib type structure can be folded and unfolded, and only occupies a small space when being folded, and the folding volume is significantly reduced.

A dynamic driving optimization method for deployable serial-parallel mechanisms in space is proposed, belonging to the field of spacecraft structural optimization design. Addressing the challenges of multi-scale high-fidelity modeling, integration of transient dynamic simulation and optimization design, lack of multi-objective collaborative optimization mechanisms in driving strategies, and insufficient model parameter calibration and robustness in existing deployable structures, this method constructs a high-fidelity dynamic model incorporating coil spring drive, rope linkage, and locking constraints. Parameter calibration is performed using experimental data, and a multi-constraint, multi-objective optimization model is established. The driving parameters are externalized, and the optimization algorithm is linked with the dynamic solver via an interface. This automatically performs parameter updates, transient simulations, and performance evaluations, iteratively obtaining the optimal set of driving parameters. Performance trade-off analysis and verification are conducted based on the optimization results. This method is applicable to the deployment driving design and performance optimization of large-scale deployable space structures.

The present application relates to the field of structural health detection, and particularly relates to a device abnormality detection method for wind-induced deformation measurement of large deployable structures, comprising the following steps: obtaining time series response data of a healthy structure under wind load excitation to form baseline reference data; and normalizing the data; combining empirical mode decomposition and Hurst index analysis to carry out signal denoising; establishing a Hankel matrix of each channel data based on the denoised data; calculating the orthogonal projection vector of the matrix; obtaining a state matrix and an output matrix of the large deployable structure through matrix decomposition; and calculating a reference mode matrix of the structure in a healthy state; in the service process of the structure, data acquisition, preprocessing and signal denoising are carried out in the same way as the above steps to obtain a current mode matrix corresponding to the service state; the distance between the current mode matrix and the reference mode matrix is calculated; the damage position of the deployable structure is determined by comparing the distance changes of each order; and the abnormality detection of the structure is realized.

This invention discloses a dual-motor driven bidirectional deployable truss structure. The dual-motor driven bidirectional deployable truss includes two motors, with multiple bidirectional deployable structural units arranged between the two motors, connected in series to form a closed loop. Each motor is connected to one bidirectional deployable structural unit via a winding mechanism, and the two motors are respectively installed at both ends of the deployable truss. This truss can effectively improve the stiffness and deployment-to-retraction ratio of the truss structure. Furthermore, the dual-motor drive, installed at both ends of the deployable truss, can effectively increase the fundamental frequency of ultra-large aperture antennas and enhance the stability of the entire structure.

The application discloses a reconfigurable foldable and deployable structure based on 3D printing and a manufacturing method thereof, and belongs to the field of additive manufacturing and intelligent structure design. The application solves the problems of existing foldable and deployable structures, such as dependence on mechanical driving and complex structure. The structure is composed of two layers of smart material plates with the same thickness. The structure combines paper cutting strategy and 3D printing to form an initial configuration with beam-hole structure in the printing stage, and realizes active foldable and deployable reconfiguration under external physical field stimulation. The manufacturing method comprises the following steps: selecting anisotropic smart material according to application scenarios, determining design parameters and beam-hole paper cutting patterns based on the theory of large deformation double-layer beam, generating 3D printing vector trajectories and integrally forming and preparing. The application does not need complex transmission assembly, and has the advantages of lightweight structure, controllable deformation, calculable design parameters, adaptation to multiple application scenarios, and application in the fields of foldable and deployable structures and flexible mechanisms.

This invention discloses an integrated wind, solar, diesel, and energy storage mobile power station, belonging to the field of mobile power station technology. It includes a transport container with two wind turbines mounted on its top surface and a weather instrument connected thereto. A diesel generator and a battery pack are housed on the inner wall of the container. Two second slide rails are fixed to the bottom of the container's interior, and a photovoltaic mechanism is horizontally mounted across the top of these rails. One side of the photovoltaic mechanism is deployable. Multiple first slide rails are sequentially connected to one end of each of the second slide rails. The deployable structure of the photovoltaic mechanism extends outward from the transport container by sliding along the first slide rails. The transport container serves as a carrier, integrating wind turbines, a weather instrument, a diesel generator, a battery pack, and a photovoltaic mechanism, achieving integrated wind, solar, diesel, and energy storage. Its compact structure facilitates mobile transportation and rapid outdoor deployment. The components work collaboratively to achieve complementarity between wind, solar, and diesel power generation, enabling it to cope with harsh environments such as windless and sunless conditions.