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Robustness analysis on aerial deployment motion of a Mars aircraft using multibody dynamics simulation: effects of wing-unfolding torque and timing

Part of: APISAT 2015

Published online by Cambridge University Press:  16 January 2017

Koji Fujita  and
Hiroki Nagai
Koji Fujita*
Affiliation:
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency, Sagamihara, Kanagawa, Japan
Hiroki Nagai
Affiliation:
Department of Aerospace Engineering, Tohoku University, Sendai, Miyagi, Japan
*
[email protected]
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Abstract

This paper investigates the effects of the design variables of an aerial deployment mechanism on the robustness of the aerial deployment through a multibody dynamics simulation. The aircraft is modelled as three joined rigid bodies: a right wing, a left wing and a centre body. A spring-loaded hinge is adopted as an actuator for deployment. The design variables are the hinge torque and the deployment timing. The robustness is evaluated using a sigma level method. The margins for the safe deployment conditions are set for the evaluation functions. The dispersive input variables are the initial drop velocity, the surrounding gust velocity, the initial pitch angle and the initial height. The design point with a deployment torque scale value F of 0.7 and a right-wing deployment delay time TSR of 1.0 s can safely deploy in the low-torque deployment condition. This design point is able to accomplish both a safe deployment and a lightweight deployment mechanism.

Keywords

aerial deploymentdeployment mechanismdesignfolding wingMars aircraftmultibody dynamics simulationrobustness
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1238 , April 2017 , pp. 449 - 468
Copyright
Copyright © Royal Aeronautical Society 2017 

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Footnotes

This is an adaptation of a paper first presented at the 2015 Asia-Pacific International Symposium on Aerospace Technology in Cairns, Australia

References

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