Dynamics of an Elastically Deployable Solar Array: Ground Test Model Validation

Jorgensen, Joni R.; Louis, Ehlias L.; Hinkle, Jason; Silver, Mark; Zuckermandel, Bill; Enger, Scott

doi:10.2514/6.2005-1942

Cited by 17 publications

(11 citation statements)

References 13 publications

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“…Novel solar array and reflector antenna concepts based on the same general approach have been proposed, including the hollow solid reflector structure [5] shown in Fig. 1, the fold integrated thin-film stiffener solar array, which undergoes three different folding stages to achieve a highly compacted configuration [6], and the folding large antenna tape-spring radar concept [7].…”

mentioning

confidence: 99%

Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Mallikarachchi

Pellegrino

2011

Journal of Spacecraft and Rockets

111

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Deployable structures made from ultrathin composite materials can be folded elastically and are able to selfdeploy by releasing the stored strain energy. This paper presents a detailed study of the folding and deployment of a tape-spring hinge made from a two-ply plain-weave laminate of carbon-fiber reinforced plastic. A particular version of this hinge was constructed, and its moment-rotation profile during quasi-static deployment was measured. The present study is the first to incorporate in the simulation an experimentally validated elastic micromechanical model and to provide quantitative comparisons between the simulations and the measured behavior of an actual hinge. Folding and deployment simulations of the tape-spring hinge were carried out with the commercial finite element package Abaqus/Explicit, starting from the as-built unstrained structure. The folding simulation includes the effects of pinching the hinge in the middle to reduce the peak moment required to fold it. The deployment simulation fully captures both the steady-state moment part of the deployment and the final snap back to the deployed configuration. An alternative simulation without pinching the hinge provides an estimate of the maximum moment that could be carried by the hinge during operation. This is about double the snapback moment.

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mentioning

confidence: 99%

Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Mallikarachchi

Pellegrino

2011

Journal of Spacecraft and Rockets

111

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“…Kuang et al (2004) investigated the dynamic behaviour of the system during solar panel deployment and the results were compared with approximate analytical solutions. Jorgensen and Louis (2005) studied the deployment dynamics of an elastically deployable solar array using analytical, computational and experimental methods. Kote et al (2007) analyzed the influence of deployment and latching of solar panel on spacecraft's attitude by deriving the equations of motion with Lagrangian formulation and solving the equations using numerical method.…”

Section: Introductionmentioning

confidence: 99%

Attitude motion of spacecraft during oblique solar panel deployment

Bai

Zhao

2012

Aircraft Engineering and Aerospace Technology

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Purpose -The purpose of this paper is to establish the dynamics model of spacecraft during deployment of oblique solar panel using Auto Dynamic Analysis of Mechanical System (ADAMS) and to study the attitude motion of the spacecraft system during the oblique solar panel deployment. Design/methodology/approach -For the case of an oblique solar panel on spacecraft, the dynamics virtual prototype model of deployment of oblique solar panels on spacecraft is established and the dynamics simulation is carried out using ADAMS. The effects of solar panel deployment on the attitude motion of spacecraft with different oblique angles are studied and the attitude motion regularities of spacecraft system are discussed. First, the effects on attitude motion of spacecraft are compared between the normal solar panel deployment and oblique solar panel deployment on a spacecraft. Then the attitude motion of spacecraft during the deployment of solar panel with different oblique angles on spacecraft is studied. Findings -The effects of oblique angle of solar panel deployment on the attitude motion of spacecraft are significant in yaw axis. The bigger the oblique angle, the bigger the changes of yaw angle of spacecraft. However, the bigger the oblique angle, the smaller the changes of roll angle of spacecraft. The effects of oblique angle on pitch angle of spacecraft are slight. Practical implications -Providing a practical method to study the attitude motion of spacecraft system during deployment of solar panel and improving the engineering application of spacecraft system, which put forward up spacecraft system to the practical engineering. Originality/value -The paper is a useful reference for engineering design of a spacecraft attitude control system and ground text.

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“…12). The structure was then deployed under quasi-static conditions, in three stages, with gravity compensation through a suspension system (Jorgensen et al, 2005).…”

Section: Model Validationmentioning

confidence: 99%

“…Later, curved large tape springs were applied to an ultra-thin shell deployable reflector (Soykasap et al, 2012). The dynamics of an elastically deployable solar array made by the combination of CFRP sheets and tape springs was analyzed and validated through the ground test model (Jorgensen et al, 2005). Marks et al (2002) designed and analyzed a lightweight deployable antenna for the Mars advanced radar for subsurface and ionospheric sounding (MARSIS) experiment on the Mars express spacecraft.…”

Section: Introductionmentioning

confidence: 99%

Design and analysis of bidirectional deployable parabolic cylindrical antenna

Fu-ling

Dai

2014

J. Zheijang Univ.-Sci.

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Abstract:A bidirectional deployable parabolic cylindrical reflector for an L-band synthetic aperture radar is presented in this study, in which a self-deployed antenna with low weight was designed. The antenna consists of four curved surfaces formed from thin sheets of composite materials connected by hinges along the edges, and the reflective surface is provided by the front surface. The edge profiles of connecting lines were obtained through geometric analysis. A scaled model, including design and manufacture, was demonstrated to validate the process from the folded state to the fully deployed state. The non-contact synchronous vision measuring method was used to test the basic frequency of the scaled model, and the test results gave the verification of the analyses. Compared with the existing unidirectional deployable antenna, this new type of bidirectional deployable antenna can be applied to larger-size antennas and has better performance because the glass-woven tape connections were substituted with more reliable hinges. Static, modal, harmonic response, and transient response analyses of the full-sized reflector structure were modeled with the commercial finite element (FE) package ABAQUS. The modeling techniques were developed to predict the structural dynamic behavior of the reflector and the results showed that the first natural frequency was 0.865 Hz, and the reflector structure had good stiffness in three directions. This proposed structure has very high stiffness-to-mass ratio because of its hollow solid construction. A preliminary simulation of radiation properties of the parabolic cylindrical antenna, fed by an off-set linear feed horn array, was conducted to obtain the radiation pattern of the feed and the reflector.

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Dynamics of an Elastically Deployable Solar Array: Ground Test Model Validation

Cited by 17 publications

References 13 publications

Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Quasi-Static Folding and Deployment of Ultrathin Composite Tape-Spring Hinges

Attitude motion of spacecraft during oblique solar panel deployment

Design and analysis of bidirectional deployable parabolic cylindrical antenna

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