The design of this active hinge comes from a common idea of replacing the classical torsion-spring joint mechanisms between two panels with active hinges, the overall layout of new active joint mechanism and solar panels integrated system is shown in Fig.1 adopts the method of electromagnetic direct drive, which is installed between adjacent solar
This investigation addresses the problem of deployment of a solar array on a satellite. For this purpose, the solar panel is considered as a rigid multibody system and DC motors are used for the final desired configuration. Each one of the rotating axes necessary for the task is provided with a light actuator. The mathematical model is
Design of Solar Panels •Mechanical parts of the Solar Array •Hinges, Torsion Springs •Tie Down and other mechanical items •Substrate selection •Solar cells, connectors, sensors •Thermal knife and associated circuitry •Design extension to meet
In this paper, the complete design of a new Multi-Variant Solar Panel Deployment System in a Satellite is proposed, where I have inculcated various deployment methods and proposed a new method of satellite deployment. The complete design is done in the Autodesk 360 software (Educational license) where the
This paper will discuss in detail the design and successful implementation of Integrated Solar Panel Deployment Mechanism (ISPDM) using torsion springs and micro-levers. The design is not only in accordance with Cubesat Design Specifications (CDS) but also assures minimal extra mass and the best utilization of a three unit CUBESAT''s area.
In this paper, a PocketQube solar panel deployment and tracking system will be presented. The system is designed for a 3P PocketQubes. During the designing phase, trade-off analysis is done to meet the balance of weight, dimension and efficiency. Reliability, manufacturability, and cost are also considered from the beginning, as
Allen, G., Othmane, B.: Design and development of CubeSat solar array deployment mechanisms using shape memory alloys. In: Proceedings of the 44th Aerospace Mechanisms Symposium (2018) Tae-Yong, P., Bong-Geon, C., Hyun-Ung, O.: Development of 6 U CubeSat''s deployable solar panel with burn wire triggering holding and release mechanism.
A new solar panel deployment mechanism for nano-satellites is developed and successfully deployed on-orbit with an objective of achieving modularity and optimization in terms of mass and volume...
To deploy solar arrays safely, several deployment performances such as low latch-up load, latching without overshoot, high deployment stiffness, and high torque margin are typically considered. To satisfy these requirements, various types of hinges—flexible or rigid—have been applied to deployment devices for a solar array [1]. The most
DOI: 10.1016/J.AST.2015.06.013 Corpus ID: 107239834; Systematic design of tape spring hinges for solar array by optimization method considering deployment performances @article{Kim2015SystematicDO, title={Systematic design of tape spring hinges for solar array by optimization method considering deployment performances}, author={Kyung Won Kim and
To make the correlation of deploying panels between test and analysis, the dynamic equation of the deploying solar arrays was derived and the motion was compared with the deployment test result of
In this paper, the complete design of a new Multi-Variant Solar Panel Deployment System in a Satellite is proposed, where I have inculcated various deployment methods and proposed a new method of satellite deployment. The complete design is done in the Autodesk 360 software
The novel three-pogo pin-based HRM has several advantages, including high loading capability in launch configuration, simpler electrical system, and guaranteed solar panel deployment in a space environment. In addition, the radiation test results of the electrical interface PCB confirmed the radiation hardness of the P-HRM to deploy the solar
Abstract—In this paper, a detailed design and simulation process of solar array deployment
Tracking the sun''s path is one of the efficient measures that may be adopted to improve the panel performance. Several researchers have investigated many different tracking mechanisms [4, 5].The physical solar tracking system construction (Fig. 10.1a, b) and its system performance depended on the choice of hardware, firmware and mechanical operation of the
The solar panel deployment mechanism includes two parts (see Fig. 1); (1) an active hinge which provides the kinetic energy of deployment by two redundant torsional springs, (2) a passive hinge which controls the rotational speed by means of a brushed DC motor and undergoes locking in the intended position when the solar panel deployment phase
This paper presents an innovative method to control the rotational speed of a satellite solar panel during its deployment phase. A brushed DC motor has been utilized in the passive spring...
This is normally implemented by a new design, such as a novel design of the composite structural lattice frame for the spacecraft solar arrays, 5 and a tape spring hinge designed by an optimization method for the
The Solar Panel Deployment project aims to design a functional deployment mechanism for the solar panels on the 2U satellite from the UCI CubeSat team. The goal is to design, manufacture, and test a prototype version of the deployment device to be used on the CubeSat team''s satellite. Objectives: Ensure that the mechanism consistently deploys
Abstract – Solar array rotation mechanism provides a hinged joint between the solar panel and satellite body, smooth rota-tion of the solar array into deployed position and its fixation in this position. After unlocking of solar panel (while in orbit), rotation bracket turns towards ready-to-work position under the action of driving spring.
It is an experimental design based on the Microcontroller that triggers the linear actuator when the panel receives signals from the controller to tilt the solar panel according to the sun''s
Abstract – Solar array rotation mechanism provides a hinged joint between the solar panel and
The novel three-pogo pin-based HRM has several advantages, including high loading capability in launch configuration, simpler electrical
Abstract—In this paper, a detailed design and simulation process of solar array deployment mechanism (SADM) for a large remote sensing satellite is presented. The mechanism is composed of three main assemblies; i) hinge assembly with torsion springs responsible for the mechanism rotation, and solar panel stoppage at
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