Optimal Design of Two-Stage-To-Orbit Space Planes with Airbreathing Engines

Abstract

Many candidate concepts of reusable space transportation vehicles have been proposed around the world. Our aim in this study is to apply an optimization method for conceptual designs of two-stage-to-orbit (TSTO) space planes with airbreathing engines on the first-stage boosters and to obtain necessary vehicle sizes and their optimal flight trajectories. First, we integrate analysis methods into the optimization problem, the solution of which yield the minimized total dry mass of the first-stage booster and the second-stage orbiter. This information allows us to determine the optimal vehicle configuration and flight trajectory for a highly feasible TSTO space plane. The optimal solutions show that TSTO space planes with boosters powered by rocket engines added to the airbreathing engines are lighter in total dry mass than vehicles with boosters propelled by only airbreathing engines. However, it is necessary to lighten and miniaturize vehicle components to achieve greater feasibility. In addition, the trajectory optimizations enable the booster to glide back to a launch site using little propellant, despite the long downrange path from the staging point of the ascent trajectory. This study confirms that the analysis and optimization method proposed are effective.

Multidisciplinary design optimization of an expendable launch vehicle

“…Using this GA and the objective function, in 2003 and 2006, Burkhalter, Jenkins, and Hartfield took the design optimization of missile systems further [3][4][5]. Significant research has been performed in rocket-based vehicle design optimization using various evolutionary techniques [6][7][8][9][10][11][12][13][14][15][16]. Cost has also been considered in some studies [17][18][19] [20].…”

Multidisciplinary Design Optimization of Long or Short Range Hypersonic Aircraft

“…The use of an MDO approach is of particular importance in the field of aircraft design because of the multidisciplinary and complex nature of aircraft (e.g., aerodynamics, structure, propulsion, trajectory, controls, cost and operations). The applications of MDO techniques have offered a great advantage in the conceptual design of unconventional aircraft, 1) space planes, 2,3) and hypersonic vehicles [4][5][6][7] because of the inadequateness of conventional rendering techniques for their design. The conceptual design of these vehicles pushes the limitations of current technologies.…”

Trajectory Optimization and Conceptual Study of Small Test Vehicles for a Hypersonic Engine Using a High-Altitude Balloon

“…Incidentally, the hypersonic engines are expected to be used as airbreathing engines of future reusable space transportation vehicles, spaceplanes. 2,3) A promising candidate for such engines is a precooled turbojet (PCTJ) engine. We have studied the components of the PCTJ engine, 3,4) and our next step is to examine the engine in an actual flight environment.…”