Dynamic analysis of a deployable space structure

Weeks, G. E.

doi:10.2514/6.1985-593

Cited by 2 publications

(3 citation statements)

References 3 publications

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Section: Introductionmentioning

confidence: 99%

“…Weeks developed a mathematical model and a corresponding simulation code for investigating the free-vibration and forced-response behavior of a deployable space structure. 18 To deal with the effects of joint clearance on the dynamic performance, Li et al proposed a virtual experimental modal analysis method. 19 In future, the space missions, such as acquisition of highresolution images, space surveillance, or target identification, require more precision deployable structures.…”

Section: Introductionmentioning

confidence: 99%

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Accuracy analysis of a multi-closed-loop deployable mechanism

Yang

Luo

Zhang

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part C:

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The multi-closed-loop deployable mechanism generates distortion which is caused by the deviation of each rod after being assembled as a result of manufacturing error, which leads to the degradation of the antenna performance or excess of the given envelope. The multi-closed-loop deployable mechanisms consist of many closed loops and have complicated topology structure and loop constraints coupling. The positioning accuracy analysis of such mechanism is more difficult than the open-chain mechanisms or the single-loop mechanisms. In order to solve this problem, first, based on the minimum of elastic deformation energy, the distortion analysis model is constructed. Second, the sensitivity of the mechanism distortion to the individual rod deviation is investigated by examining the Lagrange multipliers. By means of this model, the allowable tolerance of multi-closed-loop deployable mechanism is discussed and calculated. Last but not least, the above method and model are applied to the four-closed-loop deployable mechanism to solve the problems of its distortion, sensitivity, and tolerance in both fully deployed and folded configurations. It is demonstrated in this paper that the model and method proposed are well accommodated to the accuracy analysis of such mechanisms. The achievement of the research will help reduce the difficulties of the assembling and manufacturing of the multi-closed-loop deployable mechanisms.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Accuracy analysis of a multi-closed-loop deployable mechanism

Yang

Luo

Zhang

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part C:

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“…The author has applied it to systems without constraints and with constraints using Lagrange multipliers. The matrix representation of the derivation is included.Weeks [9] has discussed the dynamicanalysis of a deployable exiblesolar array with a coilable lattice boom stiffener. The solar array is modelled as a membrane, with the boom modelled as a beam.…”

Section: Introductionmentioning

confidence: 99%

Matrix approach to deployment dynamics of an n-panel solar array

Balaji

Nataraju

Sureshakumar

2003

Proceedings of the Institution of Mechanical Engineers, Part K:

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The equations of motion of a deploying solar array are derived using Lagrange's method and solved numerically. With increase in the number of panels, the mathematical modelling becomes complicated, invo1ving the derivation of lengthy equations which can be error prone. A matrix approach has been adopted for automatic derivation of lengthy equations of motion. This facilitates the accommodation of n panel formulation by increasing the number of rows and columns. The complexity in derivation of the air drag and damper are discussed here. NOTATION A p projected area (m 2 ) B r width of the panel (m) c prerotation angle of the torsion springs (rad) C d drag coef cient i, j subscripts de ning the yoke and the panels 1 4 …i; j † 4 n I mass moment of inertia (kg m 2 ) K stiffness of the spring (N m/rad) K c stiffness of the Closed Control Loop (CCL) springs (N/m) ‰KŠ generalized stiffness matrix K T stiffness of the torsion spring at each hinge line (N m/rad) l length of the yoke and panels (m) L Lagrangian …T ¡ U † m mass of the yoke and panels (kg) ‰M Š generalized inertia matrix n number of panels ‰N Š Coriolis/centripetal acceleration matrix q generalized coordinates (rad) _ q q rst derivative of q with respect to time (rad/s) q q second derivative of q with respect to time (rad/s 2 ) fQ i g generalized force vector (N m) R p radius of the CCL pulley (m) t time (s) T total kinetic energy of the system (N m) U total potential energy of the system (N m) U c potential energy of the CCL pulley (N m) v system velocities (m/s) x distance from the hinge line to the elemental strip (m) dW total virtual work (N m) r density of air (kg/m 3 )

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Dynamic analysis of a deployable space structure

Cited by 2 publications

References 3 publications

Accuracy analysis of a multi-closed-loop deployable mechanism

Accuracy analysis of a multi-closed-loop deployable mechanism

Matrix approach to deployment dynamics of an n-panel solar array

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