Technology and staging effects on two-stage-to-orbit systems

Trajectory Optimisation of a Partially-Reusable Rocket-Scramjet-Rocket Small Satellite Launch System

“…LaRC Turboramjet [24] The LaRC boosters were developed by Wilhite et al [24] in order to test the effects of staging Mach number on a two-stage system.…”

“…However, their development cost is likely to be very high, and they are generally suited for launching large amounts of payload-to-orbit [15][16][17][18][19][20][21][22], a market which is now extremely competitive thanks to the relatively recent advent of large, partially reusable, rocket-based launch systems. Alternatively, the launcher may be separated into multiple stages, similarly to typical, fully rocket-based launch systems [24][25][26][27][28][29][30][31][32][33]. Multi-stage airbreathing launch systems have the potential to bring cost-efficient reusability to small payload launchers [12], particularly if they are able to stage at high speeds [23].…”

“…There are as of yet no airbreathing launch systems that have progressed past the research and very early design stages [15][16][17][18][19][20][21][22][24][25][26][27][28][29][30][31][32][33]. The development and analysis of trajectories is a crucial part of this early design process, and it is a complex task to ensure that an airbreathing launch system is able to survive launch and fly with maximum efficacy.…”

“…Compared to single-stage airbreathing systems, multi-stage airbreathing launch system trajectories are far more complex, with even more complex trade-offs between the operational modes due to these modes being separated into mechanically distinct stages [34]. There is considerable disparity between studies of two-stage-to-orbit airbreathing launch system trajectories, with significant differences in the shape of the airbreathing flight [24][25][26][27][28][29][30][31][32][33]. The return trajectories of two-stage-to-orbit launch systems are generally performed under cruise power, utilising turbojet, or sometimes ramjet engines [24,26,30,31], or alternatively landing at a point downrange [27].…”

“…There is considerable disparity between studies of two-stage-to-orbit airbreathing launch system trajectories, with significant differences in the shape of the airbreathing flight [24][25][26][27][28][29][30][31][32][33]. The return trajectories of two-stage-to-orbit launch systems are generally performed under cruise power, utilising turbojet, or sometimes ramjet engines [24,26,30,31], or alternatively landing at a point downrange [27]. No studies have attempted a detailed investigation into the trajectory-based performance trade-offs between the stages, and the maximum efficiency trajectories of two-stage airbreathing launch systems are not well understood.…”