Skip to main content Accessibility help
×
×
Home

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

  • Koji Fujita (a1) and Hiroki Nagai (a2)

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.

Copyright

Corresponding author

Footnotes

Hide All

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

Footnotes

References

Hide All
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.
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.
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.
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.
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 2392923945.
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 123.
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.
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_1Pk_6.
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.
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.
11. Tajima, H., Fundamentals of Multibody Dynamics, 2006, Tokyo Denki University Press, Tokyo, Japan (in Japanese).
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.
13. Hoerner, S.F. and Borst, H. V. Fluid-Dynamic Lift, 1975, Hoerner Fluid Dynamics, Bricktown, New Jersey, US.
14. Kato, K., Oya, A. and Karasawa, K. Introduction to Aircraft Dynamics, 1982, Tokyo University Press, Tokyo, Japan (in Japanese).
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].
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.
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 950957.
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 105112.
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.
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).
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.
Recommend this journal

Email your librarian or administrator to recommend adding this journal to your organisation's collection.

The Aeronautical Journal
  • ISSN: 0001-9240
  • EISSN: 2059-6464
  • URL: /core/journals/aeronautical-journal
Please enter your name
Please enter a valid email address
Who would you like to send this to? *
×

Keywords

Metrics

Full text views

Total number of HTML views: 0
Total number of PDF views: 0 *
Loading metrics...

Abstract views

Total abstract views: 0 *
Loading metrics...

* Views captured on Cambridge Core between <date>. This data will be updated every 24 hours.

Usage data cannot currently be displayed