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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

REFERENCES

1. Jacob, J.D. and Smith, , S.W. Design limitations of deployable wings for small low altitude UAVs, Proceedings of the 47th AIAA Aerospace Sciences Meeting Including The New Horizons Forum and Aerospace Exposition, AIAA 2009-1291, January 2009, Orlando, Florida, US.Google Scholar
2. Guynn, M.D., Croom, M.A., Smith, S.C., Parks, R.W. and Gelhausen, P. A. Evolution of a Mars airplane concept for the ARES Mars Scout Mission, Proceedings of the 2nd AIAA Unmanned Unlimited Systems, Technologies, and Operations, AIAA 2003-6578, September 2003, San Diego, California, US.Google Scholar
3. Hall, D.W., Parks, R.W. and Morris, S. Airplane for Mars exploration, NASA TR, 1997, NASA Ames Research Center, Moffett Federal Airfield, California, US.Google Scholar
4. Bovais, C. S. and Davidson, P. T. Flight testing the flying radar target (FLYRT), Proceedings of the 7th Biennial Flight Test Conference, AIAA-94-2144-CP, 279-286, June 1994, Colorado Springs, Colorado, US.Google Scholar
5. Smith, M.D., Pearl, J.C., Conrath, B.J. and Christensen, P.R. Thermal emission spectrometer results: Mars atmospheric thermal structure and aerosol distribution, J Geophysical Research, 2001, 106, (E10), pp 23929–23945.Google Scholar
6. Rafkin, S.C.R. and Michaels, T.I. Meteorological predictions for 2003 Mars exploration rover high-priority landing sites, J Geophysical Research, 2003, 108, (8091), pp 1–23.Google Scholar
7. Fujita, K., Motoda, T. and Nagai, H. Numerical analysis for an aerial deployment motion of a folded-wing airplane, Proceedings of the AIAA SciTech2014, AIAA 2014-0383, January 2014, National Harbour, Maryland, US.Google Scholar
8. Fujita, K., Motoda, T. and Nagai, H. Dynamic behaviour of Mars airplane with folded-wing deployment, Transactions of JSASS Aerospace Tech Japan, 2014, 12, No. ists29, pp Pk_1–Pk_6.Google Scholar
9. Fujita, K., Motoda, T. and Nagai, H. Flow-coupled multibody dynamics simulation for an aerial deployment of a folded wing, Proceedings of the 10th International Conference on Flow Dynamics, OS13-54, November 2013, Sendai, Japan.Google Scholar
10. Fujita, K., Motoda, T. and Nagai, H. Aerial-wing-deployment simulation of the folded-wing airplane with individual aerodynamic characteristics, Proceedings of the 2013 Asia-Pacific International Symposium on Aerospace Technology, 03-05-2p, November 2013, Takamatsu, Japan.Google Scholar
11. Tajima, H., Fundamentals of Multibody Dynamics, 2006, Tokyo Denki University Press, Tokyo, Japan (in Japanese).Google Scholar
12. Okamoto, M. and Azuma, A. Aerodynamic characteristics at low Reynolds numbers for wings of various planforms, AIAA J, 2011, 49, (6), pp 1135-1150.Google Scholar
13. Hoerner, S.F. and Borst, H. V. Fluid-Dynamic Lift, 1975, Hoerner Fluid Dynamics, Bricktown, New Jersey, US.Google Scholar
14. Kato, K., Oya, A. and Karasawa, K. Introduction to Aircraft Dynamics, 1982, Tokyo University Press, Tokyo, Japan (in Japanese).Google Scholar
15. NASA, Glenn Research cCnter, Aerodynamics Index, Mars Atmosphere Model Metric Units, URL: http://www.grc.nasa.gov/WWW/K-12/airplane/atmosmrm.html [cited 16 November 2016].Google Scholar
16. Shampine, L.F. and Gordon, M. K. Computer Solution of Ordinary Differential Equations: the Initial Value Problem, 1975, W.H. Freeman, San Francisco, California, US.Google Scholar
17. Shimoyama, K., Oyama, A. and Fujii, K.A. New efficient and useful robust optimization approach–design for multi-objective six sigma, Proceedings of the 2005 IEEE Congress on Evolutionary Computation, Vol. 1, 2005, pp 950–957.CrossRefGoogle Scholar
18. Shimoyama, K., Jeong, S. and Obayashi, S. Methodology development and real-world application for multi-objective robust design, J Reliability Engineering Association of Japan, 2010, 32, (2), (in Japanese), pp 105–112.Google Scholar
19. Shimoyama, K. Robust aerodynamic design of Mars exploratory airplane wing with a new optimization method, PhD Dissertation, 2006, School of Engineering, University of Tokyo, Japan.Google Scholar
20. Takeuchi, S., Yonemoto, K., Iwata, M., Narumi, T., Matsumoto, T., Fukuda, K., Uchida, J. and Kato, E. Conceptual structure design of Mars exploration airplane, Proceeding of the 49th Aircraft Symposium, JSASS-2011-5228, October 2011, Kanazawa, Japan (in Japanese).Google Scholar
21. Nagai, H., Oyama, A. and Mars Airplane WG. Development of Mars exploration aerial vehicle in Japan, Proceeding of the 30th International Symposium on Space Technology and Science, 2015-k-46, July 2015, Kobe, Japan.Google Scholar