Skip to main content Accessibility help
×
Home

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

  • L. Zhang (a1), M. Sun (a2), Q. Cheng (a1), Z. Chen (a2) and X. Zhang (a3)...

Abstract

The takeoff-mass of a two-stage-to-orbit Rocket-Based Combined Cycle Engine-Rocket (RBCC-RKT) launch vehicle is a crucial factor in its comprehensive performance. This paper optimizes the takeoff-mass together with the trajectory by reformulating it to a nonlinear optimal control problem. The range of the second stage rocket mass is considered as a process constraint. When the scopes of initial and terminal states are specified, the problem can be solved by using the Gauss pseudo-spectral method (GPM). In order to reduce the convergent difficulty caused by using table data, the data in different stages are utilized by employing an integrated interpolation strategy through the optimization. Simulation results show that the mass can be effectively optimized to meet the inertia mass ratio constraint of the first-stage, and the separation of Mach number and altitude can be optimized at the same time.

Copyright

Corresponding author

References

Hide All
1.Fujikawa, T., Tsuchiya, T. and Tomioka, S. Multi-objective, multidisciplinary design optimization of TSTO space planes with RBCC Engines, Aiaa/asce/ahs/asc Structures, Structural Dynamics, & Materials Conference, 59 January 2015, Kissimmee, Florida 2015.
2.Cheng, F., Tang, S., Zhang, D. and LI, Y. Quasi-one-dimensional modeling and analysis of RBCC dual-mode Scramjet engine, Int J Turbo and Jet Engines, 2017, 36, (2), 195206.
3.Chae, S.H., Kim, H.S., Yee, K.J., Oh, S.J. and Choi, J.Y. Design optimization and analysis of a RBCC engine flowpath using a Kriging model based genetic algorithm, J Korean Soc Propulsion Engineers, 2017, 21, (1), pp 5162.
4.Olds, J.R. and Mccormick, D.J. Component-level weight analysis for RBCC engines, American Institute of Aeronautics and Astronautics, American Institute of Aeronautics and Astronautics, Huntsville, AL, USA 1997.
5.Etele, J., Hasegawa, S. and Ueda, S. Experimental investigation of an alternative rocket configuration for rocket-Based combined cycle engines, J Propulsion and Power, 2014, 30, (4), pp 944951.
6.Ruan, J.Q. and Lv, X. Takeoff mass estimation methods in two-stage-to-orbit RBCCRKT launch vehicle, J Propulsion Technology, 2013, 34, (5), pp 603608.
7.Lu, X., He, G.Q. and Liu, P.J. Ascent trajectory design method for RBCC-powered vehicle, Acta Aeronautica et Astronautica Sinica, 2010, 31, (7), pp 13311337.
8.Jiang, Y.Z., Jiang, C.W. and Gao, Z.X. Mass estimation method and its application for horizontal-takeoff horizontal-landing two-stage-to-orbit system, J. Beijing University of Aeronautics and Astronautics, 2013, 34, (12), pp 17.
9.Chojnacki, K.T. and Clark, W.H. An assessment of the Rocket-Based Combined Cycle propulsion system for Earth-to-orbit transportation, Joint Propulsion Conference and Exhibit (Vol. 1), 2830 June 1993, Monterey, CA, U.S.A. 1993.
10.Pimentel, J. Development of an online database tool for quick access to mass estimating relationships, Doctoral dissertation, Georgia Institute of Technology, 2004.
11.Zhang, L.M., Gao, H.T., Chen, Z.Q., Sun, Q.L. and Zhang, X.H. Multi-objective global optimal parafoil homing trajectory optimization via Gauss pseudospectral method, Nonlinear Dynamics, 2013, 72, (3), pp 18.
12.Benson, D. A Gauss pseudo-spectral transcription for optimal control, Doctoral dissertation, Massachusetts Institute of Technology, 2004.
13.Fahroo, F. and Ross, I.M. Costate estimation by a Legendre pseudospectral method, J. Guidance, Control, and Dynamics, 2001, 24, (2), pp 270277.
14.Davies, C.J., Gubbins, D. and Jimack, P.K. Scalability of pseudospectral methods for geodynamo simulations, Concurrency Computation Practice and Experience, 2011, 23, (1), pp 3856.
15.Huntington, G.T. Advancement and analysis of a Gauss pseudo-spectral transcription for optimal control problems, Doctoral dissertation, University of Florida, 2007.
16.Meyer, M.L., Chato, D.J., Plachta, D.W., Zimmerli, G.A., Barsi, S.J., Van Dresar, N.T. and Moder, J.P. Mastering cryogenic propellants, J. Aerospace Engineering, 2012, 26, (2), pp 343351.
17.Daidzic, N.E. High-elevation equatorial catapult-launched RBCC SSTO spaceplane for economic manned access to LEO. Int J Aviation, Aeronautics, and Aerospace, 2016, 3, (2), p 4.
18.Brock, M.A. and Captain, B.M. Performance study of two-stage-to-orbit reusable launch vehicle propulsion alternatives, Afit /Gss /Eny /04-M02, 2004.
19.Olds, J. and Bradford, J. Sccream (Simulated Combined Cycle Rocket Engine Analysis Module): A conceptual RBCC engine design tool, AIAA 97-2760, 1997.
20.Shaughnessy, J.D., Pinckney, S.Z., Mcminn, J.D., Cruz, C.I. and Kelley, M.L. Hypersonic vehicle simulation model: Winged-Cone configuration, NASA TM-102610, 1990.
21.Ruan, J.Q., He, G.Q. and Lv, X. Trajectory optimization method in two-stage-to-orbit RBCC-RKT launch vehicle, Acta Aeronautica ET Astronautica Sinica, 2014, 35, (5), pp 12841291.
22.Conn, A.R., Gould, N.I.M. and Toint, P.L. A globally convergent augmented Lagrangian algorithm for optimization with general constraints and simple bounds, Siam J Numerical Analysis, 1989, 28, (2), pp 545572.
23.Tawfiqur, R. and Zhou, H. Trajectory optimization of hypersonic vehicle using gauss pseudo-spectral method, Int Conf Mechanical and Electrical Technology, 2011, 13, pp 329334.
24.Ghorbani, M.T. and Salarieh, H. Optimal tracking control of an under actuated container ship based on direct Gauss pseudo-spectral method, Scientia Iranica. Transaction B, Mechanical Engineering, 2014, 21, (6), pp 19731980.
25.Singer, M.A. and Pope, S.B. Exploiting ISAT to solve the equations of reacting flow, Combustion Theory and Modelling, 2004, 8, 361383.
26.Benson, D.A., Huntington, G.T., Thorvaldsen, T.P. and RAO, A.V. Direct trajectory optimization and costate estimation via an orthogonal collocation method, J Guidance, Control, and Dynamics, 2006, 29, (6), pp 14351440.
27.Lei, W., Jianquan, G.E., Tao, Y., Zhiwei, F. and Zhengnan, L.I. Multi-objective trajectory optimization for hypersonic glide vehicle using boundary intersection method, J National University of Defense Technology, 2016, 38, (4), pp 137142.
28.Das, I. and Dennis, J.E. Normal boundary intersection: a new method for generating Pareto surface in nonlinear multicriteria optimization problems, SIAM J Optimization, 1998, 8, (3), pp 631657.
29.Logist, F., Houska, B., Diehl, M. and Van Impe, J. Fast Pareto set generation for nonlinear optimal control problems with multiple objectives, Structural and Multidisciplinary Optimization, 2010, 42, (4), pp 591603.
30.Chiu, S.K. Multidimensional interpolation using a model-constrained minimum weighted norm interpolation, Geophysics, 2014, 79, (5), pp V191V199.
31.Pini, M., Spinelli, A., Persico, G. and Rebay, S. Consistent look-up table interpolation method for real-gas flow simulations, Computers and Fluids, 2015, 107, pp 178188.

Keywords

Integral performance optimization for the two-stage-to-orbit RBCC-RKT launch vehicle based on GPM

  • L. Zhang (a1), M. Sun (a2), Q. Cheng (a1), Z. Chen (a2) and X. Zhang (a3)...

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