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

Published online by Cambridge University Press:  17 June 2019

L. Zhang ,
M. Sun ,
Q. Cheng ,
Z. Chen  and
X. Zhang
L. Zhang*
Affiliation:
School of Mechanical Engineering Liaoning Technical UniversityFuxin, China
M. Sun
Affiliation:
Tianjin Key Laboratory of Intelligent Robotics Nankai UniversityTianjin, China
Q. Cheng
Affiliation:
School of Mechanical Engineering Liaoning Technical UniversityFuxin, China
Z. Chen
Affiliation:
Tianjin Key Laboratory of Intelligent Robotics Nankai UniversityTianjin, China
X. Zhang
Affiliation:
College of Electrical Engineering Tianjin Sino-German University of Applied SciencesTianjin, China
*
limin_1107@ yahoo.com
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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.

Keywords

Gauss pseudo-spectral methodMass estimationRBCCTwo-stage-to-orbitConstraint
Type
Research Article
Information
The Aeronautical Journal , Volume 123 , Issue 1265 , July 2019 , pp. 945 - 969
Copyright
© Royal Aeronautical Society 2019 

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