Deployable Antenna Research Articles

Research on Damping Mechanism with Resetting Capability for Axial Vibration Control of Satellite Antenna

With the development of space technology, the large scale space deployable antennas gradually become one of the key research themes of research. The basic requirements for large scale satellite antennas are the characteristics of light in weight and high in profile accuracy. The low-frequency and large-amplitude vibration of the large scale antennas is easily excited when working in an environment with zero gravity. In order to suppress the vibration of large scale deployable satellite antenna, a new type of damping mechanism with resetting capability is presented to improve the ability of vibration energy consumption and ensure the dynamic characteristics of the radial rib structure containing the presented profile accuracy of the antenna. The rod making up the deployment mechanism of the antennas is divided into two parts which connected by using the shape memory alloy (SMA) wires through guiding mechanism. Meanwhile, a metal rubber is fixed and pressed between two parts of the rod by SMA wires. The ability of the friction energy dissipation of the metal rubber is utilized to suppress the axial vibration of the rods. The super elasticity of the SMA wires is used to provide the restoring force for ensuring the dimensional stability of the rod. In this paper, the design principle of the axial self-resetting damping structure is introduced in detail. And, the dynamic characteristics of the radial rib structure containing the presented damping mechanism are investigated by using the software ANSYS. The simulation results show that the vibration amplitude of the radial rib of antennas has been reduced significantly.

Passive UHF RFID Network Planning for Accurate 3-D Location via Restricted Genetic Algorithm

Indoor localization via radio-frequency identification (RFID) carries critical importance due to its high accuracy and low hardware requirement. The positions of reader antennas can affect the positioning accuracy and coverage in RFID network. In this letter, we present a novel RFID network planning (RNP) approach to optimize the deployment of reader antennas for accurate 3-D location. First, the 3-D antenna radiation mode of a passive UHF RFID system is set up. Then, the received signal strength (RSS) and path loss characteristics (PLC) are analyzed and a restricted genetic algorithm (RGA) is developed to obtain the optimal solution of the RNP via maximizing the total reward function with constraints. Finally, the convolutional neural network (CNN) and weighted <inline-formula xmlns:mml="http://www.w3.org/1998/Math/MathML" xmlns:xlink="http://www.w3.org/1999/xlink"> <tex-math notation="LaTeX">$K$ </tex-math></inline-formula> -nearest neighbor (WKNN) algorithms are respectively used to verify the localization effect. For comparison, the Cramér-Rao lower bound (CRLB) is also derived. The experimental results show that the proposed approach can improve the positioning accuracy as well as the coverage, and enhance the anti-noise capability of the location system.

Application of a New-type Damping Structure for Vibration Control in Deployment Process of Satellite Antenna Component

Vibration control of flexible deployable mechanism is seriously significant with the increasing application of it in aerospace field. Satellite antenna must be carried out in folded state due to small space of launch vehicle. In the process of deployment and attitude adjustment, vibration has a great influence on the contour accuracy. Based on transfer matrix method, the deployment structure of large flexible deployable satellite antenna is analysed to obtain its natural frequencies and modes. By solving the first three natural frequencies and modes in different deployment angles, the structure completely deployed is prone to be coupled and has the worst stability. Thus, damping structure to suppress vibration at all modal resonance points of fully deployed satellite antenna is necessarily to be installed. A new-type damping structure, multi-petal friction damping structure with the characteristics of simple structure and wide frequency-band, is proposed in previous paper. The dynamic analysis of deployment process at different angles for deployment component with damping structure is carried out to verify the damping effect and the feasibility of damping structure as well as the rationality of theoretical analysis.

Investigation of the characteristics of rapidly deployable HF antennas taking into account the parameters of the underlying surface

Investigation of the characteristics of rapidly deployable HF antennas taking into account the parameters of the underlying surface

Mechanism design and dynamic analysis of large-scale two-dimensional deployable planar antenna

Mechanism design and dynamic analysis of large-scale two-dimensional deployable planar antenna

A Foldable Reflectarray on a Hexagonal Twist Origami Structure

In this paper, a novel deployable flat panel reflectarray antenna (RA) is designed on an origami folding pattern for Small Satellite applications. The RA aperture deploys into a hexagonal geometry that achieves an aperture efficiency of a least 60%, 10-20% higher than current rectangular apertures. The modified hexagonal twist folding structure can achieve high volume packing efficiency, which is 75%, and simple deployment with one degree of freedom. The mechanical and electromagnetic design considerations for two variations of our proposed structure, flat and offset panels, are presented. The aperture surface area of both structures is 58λ2. Both structures are designed to operate at 16 GHz and exhibit a realized gain that is greater than 26.4 dBi. Prototypes are fabricated for the two structures and measured. Measurements show good correlation with the simulations.

Lightweight and Low-Cost Deployable Origami Antennas—A Review

The art of paper folding also known as Origami plays an important role in various research areas of different scientific fields. Origami structures possess many useful characteristics such as reconfigurability, flexibility, deployability, compactness, and multi-functionality. These attributes are inevitable for modern communication systems. Additionally, they provide antenna engineers an extra degree of freedom while blueprinting next-generation designs. One of the desirable features of origami is its folding capability. Using this property, it can be transformed into a two-Dimensional (2D) sheet from a three-Dimensional (3D) structure and vice versa through external stimulus. In recent years, researchers have proposed numerous smart materials to optimize folding behavior. These smart materials extend the functionality of origami technology for designing self-folding structures required in space systems, small scale devices, and self-assembly systems. Origami structures feature many useful characteristics pertinent to modern day design challenges of communication systems such as reconfiguration, flexibility, compactness, and multifunctionality. In this work, a state of the art review is presented on conceptualization, design challenges, and fabrication of light-weight and low-cost deployable origami antennas. Furthermore, to provide critical insights deployment challenges and possible solutions are also provided. It is believed that this work will not only help peers to understand the basic working principles of different origami structures but will also lay the foundation for future research in the evolving field of origami-based antennas. Moreover, the design methodology proposed in this paper will also provide pragmatic solutions for origami antennas suitable for the harsh and rigid environments.

Thermal Distortion Compensation for Improving Electrical Performance of Reflector Antennas

Aiming at the problem of the surface accuracy and electrical performance of the antenna in space environment are reduced due to thermal deformation caused by temperature load. This paper presents a method to compensate the thermally induced shape distortion of antenna reflector by actively adjusting actuators in order to improve the electrical performance. The adjustment of each actuator is related to the local deformation of the panel. Then, taking a space deployable antenna with a diameter of 5 meters as an example, the finite element model is established. According to the range of the temperature variation in space (−180°C - 200°C), different temperature loads are applied to the antenna. The variation of electrical properties and surface accuracy is analyzed and the worst working condition is determined, and the antenna is compensated based on this condition. Then, four different electrical performance parameters are used as the optimization objectives, and the electromechanical coupling optimization model is established, and the PSO algorithm is used to optimize the actuators adjustments. The results show that the method can effectively improve the electrical performance of the deformed reflector antenna.

Performance of Partially Deployed Spaceborne Ultra-Wideband Miura-Ori Apertures

Reconfigurable and deployable antenna arrays are required communications and remote sensing onboard small satellites/CubeSats. There is also a need for packing before launch due to the limited payload space for exo-atmospheric deployments. In this context, origami-based aperture packing and unpacking is relevant and attractive for low-volume storage. However, after several physical morphing cycles, origami apertures may not maintain the performance exhibited by fixed apertures. That is, origami-based antenna arrays are likely to suffer from reduced gain and polarization purity. Therefore, physical effects caused by origami folding should be analytically incorporated into the design. This paper proposes a statistical analysis to study the gain performance of deployable ultra-wideband Miura-ori apertures by including geometrical errors inherent to a partially deployed state. A closed-form expression of the gain degradation is derived and verified using full-wave simulations.

Research Status and Prospect of Micro-gravity Environment Simulation for Space Deployable Antenna

Research Status and Prospect of Micro-gravity Environment Simulation for Space Deployable Antenna

Surface accuracy analysis for hexagonal prism modular deployable antenna

Surface accuracy analysis for hexagonal prism modular deployable antenna

Spectral Efficient Resource Allocation for URLLC in Distributed Antenna Systems

In this paper, we propose novel resource allocation algorithms for ultra-reliable and low-latency communication (URLLC) in distributed antenna systems (DASs) and discuss the effectiveness of the receive antenna deployment and multiple access strategies in fulfilling the stringent reliability and latency requirements. We analyze achievable rates and reliabilities of the DASs with orthogonal multiple access (OMA) and non-orthogonal multiple access (NOMA) by taking into account the influence of the latency constraint and the non-identical channel distributions of the distributed antennas. Based on the performance analysis, we propose novel resource allocation algorithms for fulfilling the stringent performance requirement in OMA and NOMA. The numerical simulation results provide insightful information for understanding the impacts of multiple access strategy and antenna deployment on the spectral efficiency under the reliability and latency constraints. In particular, NOMA makes it possible to deal with more transmit nodes than OMA, and more dispersed antenna deployment facilitates to achieve a target URLLC performance with less spectrum resource as the ratio of transmit nodes to receive antennas increases. Consequently, the analysis and simulation results provide the meaningful information on the network design for mission-critical applications.

Active Vibration Control of a Large Space Antenna Structure Using Cable Actuator

A large space antenna structure will inevitably vibrate due to the space thermal environment and maneuver actions of the satellite. Such vibration will last continuously and affect normal function of the antenna. Therefore, a proper vibration control method is vital to keep the shape accuracy of the structure within an acceptable range. The research object of this paper is a large deployable planar phased array antenna that uses cables as active actuators. Research contents include the optimization of actuator position and the design of control law: both of which have considered the unilateral and saturated constraints of the cable actuator. First, the finite element method is used to obtain the modal information of the structure. Then the actuator position optimization method is established by using the controllability principle and the particle swarm optimization algorithm. Second, a piecewise cost function is adopted to design the control law by combining a linear quadratic regulator with a bang–bang regulator. In the numerical simulation, the vibration control process of an antenna structure consisting of 18 lattices is simulated and analyzed. The results prove that the proposed actuator position optimization method and the control law could effectively suppress the vibration and maintain the shape accuracy of the antenna structure.

Configuration synthesis of linear foldable over-constrained deployable unit based on screw theory

According to a description of the topology structure of deployable antennas, this work proposes the configuration synthesis method of over-constrained deployable units on the basis of screw theory and conducts example analyses on the basis of an analysis method and certain design steps. First, the basics of screw theory are introduced in detail, and an over-constrained deployable unit is represented by a screw. Second, through over-constraint analysis, the kinematic pair configurations of the mechanism under over-constraint have been established. Third, according to the general process of the deployable unit with common over-constraints proposed in this paper, the example is analyzed in detail. Finally, the model is verified according to the obtained configuration synthesis results. The cubic deployable unit mechanism is obtained through 3D printing, and the folding function is tested to verify the correctness of the theoretical analysis, which can provide theoretical reference for the mechanism design of large deployable units.

Novel Surface Design of Deployable Reflector Antenna Based on Polar Scissor Structures

Space-deployable mechanisms can be used as supporting structures for large-diameter antennas in space engineering. This study proposes a novel method for constructing the surface design of space reflector antennas based on polar scissor units. The concurrency and deployability equations of the space scissor unit with definite surface constraints are derived using the rod and vector methods. Constraint equations of the spatial transformation for space n-edge polar scissor units are summarized. A new closed-loop deployable structure, called the polar scissor deployable antenna (PSDA), is designed by combining planar polar scissor units with spatial polar scissor units. The over-constrained problem is solved by releasing the curve constraint that locates at the end-point of the planar scissor mechanism. Kinematics simulation and error analysis are performed. The results show that the PSDA can effectively fit the paraboloid of revolution. Finally, deployment experiments verify the validity and feasibility of the proposed design method, which provides a new idea for the construction of large space-reflector antennas.

An ultrawide band monopole antenna using hexagonal-square shaped fractal geometry

Fractal geometry antennas are much sought after in present scenario of wireless communication due to ever increasing demand for high gain, wide bandwidth, low cost, compact size and easily deployable antennas. An ultrawide band monopole antenna using compact hexagonal-square shaped fractal geometry is proposed here, which nearly fulfils the above demands. The fractal geometry is introduced by iteration of square slots in the hexagonal radiating patch etched on a circular chunk. The proposed antenna achieves percentage bandwidth of 146% approximately ranging from to GHz with return loss of dB and voltage standing wave ratio (VSWR) less than 2. It achieves maximum peak gain of 7.2 dBi at 11.7 GHz and an average gain of 3.9 dBi in the entire operating range of frequency, efficiency of 87.57% and good radiation pattern. A prototype of simulated antenna is developed and the tested results are validated using equivalent circuit model as well. The results are in conformity with each other. Therefore, the proposed design can be used for UWB applications such as Bluetooth ( GHz), LTE ( GHz), WLAN ( GHz), 5G, WiMAX ( GHz), military communication in C-band, satellite communication in X-band and S-band.

Investigation on design methods for cable mesh configuration of deployable space antenna reflector

Mesh reflectors are always a preferable option for large size deployable antenna reflector over solid surface reflectors due to their flexibility of adjustment in minimum possible space and ability to get deployed to full configuration in space. Maintaining surface properties and accuracy are two important requirements in the design of the mesh reflector for the performance of cable network antenna reflectors. The present work considers the various design approaches for cable mesh configuration of space deployable antenna reflectors. The equal force density shape forming criteria such is applied for obtaining the desired parabolic curvature of the mesh configuration. The ring structure for the deployable mechanism is considered as rigid linkages for designing mesh configuration. A generalized numbering scheme for nodes and cable mesh link is formulated for carrying forward various shapes forming criteria which help in making an algorithm. The algorithm for a better understanding of these methods is developed using MATLAB with nodal coordinates and its connection. Mesh configuration is developed with a different number of divisions. A study is also carried out for finding the required number of divisions for a highly accurate parabolic profile for a particular band frequency. A demonstration model is developed and a comparison of the coordinates of the prototype is made with those arrived at using the model.

Development for petal-type deployable solid-surface reflector by uniaxial rotation mechanism

Deployable solid-surface reflectors have been widely employed as the main part of antennas or telescopes in space observation and communication missions. The petal-type deployable solid-surface reflector has better package ratio and deploying properties. In order to balance the contradiction between simplification for mechanism reliability and development for structural stability, the petal-type deployable solid-surface reflector has been developed by a uniaxial rotation mechanism. This uniaxial rotation mechanism is deduced to fulfill the equivalent movement of New Petal-type Deployable Solid Surface Antenna (NPDSSA) by two orthogonal rotation mechanism based on Rodrigues Rotation Formula and Euler Angle Transformation Matrices. The general expressions of axis vector and rotation angle for uniaxial rotation mechanism are obtained to conduct parametric modeling. The 1.2-m aperture reflector as a case study is analyzed to explore kinetic properties of this model and the functions of the drag spring. It is indicated that this reflector by uniaxial rotation mechanism has a simpler mechanism and better kinetic properties than the original NPDSSA.

Structural design, analysis, and experimental verification of an H-style deployable mechanism for large space-borne mesh antennas

Owing to the rapid developments in space technology, there has been a substantial increase in the demand for large-diameter and low-mass space-borne deployable antennas with high geometric stability. To meet this demand, this paper presents a novel single mobility deployable ring mechanism with a high deploy/fold ratio. This mechanism is suitable for constructing large-scale satellite deployable antennas. First, a basic truss element with a low storage height is proposed, and fundamental parameters of the deployable mechanism are analyzed. Second, a general motion analysis model of the deployment process is established, and the corresponding cable-net structure is designed. Finally, a ground experimental prototype with a diameter of 5.0 m is fabricated to demonstrate the feasibility of the proposed mechanism. Based on the experimental results, the feasibility and effectiveness of the novel deployable antenna proposed herein are verified.

Structural Dynamic Improvement for Petal-Type Deployable Solid-Surface Reflector Based on Numerical Parameter Study

Petal-type Deployable Solid-surface Reflector (PDSR) is a kind of important structure widely applied in deployable reflector antennas in aerospace engineering. The dynamic properties of this reflector structure in deployed state are significant to the reflector accuracy for antennas. However, the study of the dynamic evaluation of deployable structure with revolute joints is difficult and seldom concerned by researchers. In order to study dynamic properties of the PDSR, the Cable Replacement Method (CRM) was utilized to equivalently simulate the nonlinear structural stiffness of the revolute joint for numerical analyses. The Finite Element Model (FEM) of this reflector structure was established by commercial software ANSYS (ANSYS Inc., Canonsburg, PA, USA) and verified by the theoretical analysis and dynamic test of actual prototype model. The natural frequencies and mode shapes of deployed reflector were computed to study the influence of drag spring design parameters as stiffness, pre-tensioned force, and distance of two adjacent linkage butts. Finally, the analysis results were concluded that the drag springs between two adjacent petals can essentially improve the dynamic performance of reflector structure in deployed state. It can be a useful technical system for future engineering applications of PDSR antennas.