Share This Article:

Effect of Spacecraft Aerodynamics and Heat Shield Characteristics on Optimal Aeroassisted Transfer

Full-Text HTML Download Download as PDF (Size:413KB) PP. 307-320
DOI: 10.4236/eng.2012.46040    5,639 Downloads   8,348 Views   Citations

ABSTRACT

A spacecraft designed to operate in a planetary atmosphere must have an adequate heat shield to withstand the high heat fluxes and heat loads that are generated by aerodynamic heating. Very often, the mass of the thermal protection system is a significant fraction of the total mass of the vehicle. In contrast, performing maneuvers in the atmosphere, that would be very costly in terms of propellant consumption if they were performed completely outside of the atmosphere in a classic way, is a very attractive prospective technique. The advantages and disadvantages in terms of total mass spared must be determined. The mission investigated involves an aeroassisted coplanar transfer from a high to a low Earth orbit. The approach uses a combination of three propulsive impulses in space together with an aerodynamic maneuver in the atmosphere. The heat shield adopted is fully ablative, given the expected high values of the entering heat flux. The convenience of the aeroassisted maneuver and the influence of the parameters involved are evaluated in comparison to a conventional Hohmann transfer. In particular, a parametric analysis is performed by varying the following characteristics of the vehicle: aerodynamic efficiency, mass-to-surface ratio, deorbit impulse, and initial altitude of the orbit. The influence of the thermal protection system is examined by assessing the impact of the type of ablative material employed, the thermal safety factor, and the allowable temperature for the adhesive layer on the substructure. The analysis is conducted with a highly representative thermal model by coupling the dynamic and thermal analyses and using a genetic optimizer. The optimization methodology and the thermal model are completely original. The results indicate the importance of choosing low-density ablative materials, of adopting a suitable thermal safety factor, and of choosing high-performance adhesives. The optimal trajectories obtained correspond to a zero second propulsive impulse.

Conflicts of Interest

The authors declare no conflicts of interest.

Cite this paper

A. Mazzaracchio and M. Marchetti, "Effect of Spacecraft Aerodynamics and Heat Shield Characteristics on Optimal Aeroassisted Transfer," Engineering, Vol. 4 No. 6, 2012, pp. 307-320. doi: 10.4236/eng.2012.46040.

References

[1] A. Mazzaracchio and M. Marchetti, “A Probabilistic Sizing Tool and Monte Carlo Analysis for Entry Vehicle Ablative Thermal Protection Systems,” Acta Astronautica, Vol. 66, No. 5-6, 2010, pp. 821-835. doi:10.1016/j.actaastro.2009.08.033
[2] A. Mazzaracchio and M. Marchetti, “Coupled Aeroassisted Orbital Plane Change Manoeuvre and Thermal Protection System Optimisation,” 61st International Astronautical Congress, Prague, September 27-October 1 2010.
[3] P. Charbonneau and B. Knap, “A User’s Guide to Pikaia 1.0,” Boulder, Colorado, 1995.
[4] P. Charbonneau, “An Introduction to Genetic Algorithms for Numerical Optimization,” Boulder, Colorado, 2002.
[5] P. Charbonneau, “Release Notes for Pikaia 1.2,” Boulder, Colorado, 2002.
[6] C. Gogu, T. Matsumura, R. T. Haftka and A. V. Rao, “Aeroassisted Orbital Transfer Trajectory Optimization Considering Thermal Protection System Mass,” Journal of Guidance, Control and Dynamics, Vol. 32, No. 3, 2009, pp. 927-938. doi:10.2514/1.37684
[7] NASA Marshall Space Flight Center, “X-37 Demonstrator to Test Future Launch Technologies in Orbit and Reentry Environments,” NASA Facts, May 2003, FS-2003-05- 65-MSFC.
[8] Y. Y. Shi and D. H. Young, “Minimum Fuel Coplanar Aeroassisted Orbital Transfer Using Collocation and Nonlinear Programming,” Flight Mechanics/Estimation Theory Symposium, NASA Goddard Space Flight Center, 1991, pp. 461-480 (SEEN92-1407005-13).
[9] US Standard Atmosphere, US Government Printing Office, Washington DC, 1976.
[10] T. J. Collins, W. M. Congdon, S. S. Smeltzer and K. S. Whitley, “High-Temperature Structures, Adhesives, and Advanced Thermal Protection Materials for Next-Generation Aeroshell Design,” NASA Langley Research Center, 2006, Paper 2M-02-2005.

  
comments powered by Disqus

Copyright © 2018 by authors and Scientific Research Publishing Inc.

Creative Commons License

This work and the related PDF file are licensed under a Creative Commons Attribution 4.0 International License.