NRT Rotor Structural / Aeroelastic Analysis for the Preliminary Design Review

AbstractThe Coronal Solar Magnetism Observatory (CoSMO) is a proposed new facility led by the High Altitude Observatory and a consortium of partners to measure magnetic field and plasma properties in a large (one degree) field of view extending down to the inner parts of the solar corona. CoSMO is intended as a research facility that will advance the understanding and prediction of space weather. The instrumentation elements of CoSMO are: a white-light coronagraph (KCor), already operational at the Mauna Loa Solar Observatory (MLSO); the Chromosphere and Prominence Magnetometer (ChroMag), due for deployment to MLSO next year; and the CoSMO Large Coronagraph (LC) which has completed Preliminary Design Review.

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The instrument control unit of the PLATO payload: design consolidation following the preliminary design review by ESA

Space Telescopes and Instrumentation 2020: Optical, Infrared, and Millimeter Wave ◽

10.1117/12.2562003 ◽

2020 ◽

Author(s):

Rosario Cosentino ◽

Mauro Focardi ◽

Stefano Pezzuto ◽

Giovanni Giusi ◽

Emanuele Galli ◽

...

Keyword(s):

Control Unit ◽

Preliminary Design ◽

Design Review ◽

Instrument Control

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Preliminary Design Review: GMTI Narrowband for the Basic PCA Integrated Radar-Tracker Application

10.21236/ada419856 ◽

2004 ◽

Author(s):

A. I. Reuther

Keyword(s):

Preliminary Design ◽

Design Review

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Static Aeroelastic Beam Model Development for Folding Winglet Design

Aerospace ◽

10.3390/aerospace7080106 ◽

2020 ◽

Vol 7 (8) ◽

pp. 106

Author(s):

Bereket Sitotaw Kidane ◽

Enrico Troiani

Keyword(s):

Structural Integrity ◽

Model Development ◽

Computational Cost ◽

Weighted Average ◽

Element Model ◽

Beam Model ◽

Preliminary Design ◽

Aerodynamic Loads ◽

Aeroelastic Analysis ◽

Aeroelastic Model

Wing shape adaptability during flight is the next step towards the greening of aviation. The shape of the wing is typically designed for one cruise point or a weighted average of several cruise points. However, a wing is subjected to a variety of flight conditions, which results in the aircraft flying sub-optimally during a portion of the flight. Shape adaptability can be achieved by tuning the shape of the winglet during flight. The design challenge is to combine a winglet structure that is able to allow the required adaptable shape while preserving the structural integrity to carry the aerodynamic loads. The shape changing actuators must work against the structural strains and the aerodynamic loads. Analyzing the full model in the preliminary design phase is computationally expensive; therefore, it is necessary to develop a model. The goal of this paper is to derive an aeroelastic model for a wing and winglet in order to reduce the computational cost and complexity of the system in designing a folding winglet. In this paper, the static aeroelastic analysis is performed for a regional aircraft wing at sea level and service ceiling conditions with three degree and eight degree angle of attack. MSC Nastran Aeroelastic tool is used to develop a Finite Element Model (FEM), i.e., beam model and the aerodynamic loads are calculated based on a doublet lattice panel method (DLM).

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