Sriram Rengarajan

TL;DR: In this article, the conceptual design and performance analysis of a partially reusable space launch vehicle for small payloads is presented, which uses a multi-stage vehicle with rocket engines, with a reusable first stage capable of glided or powered flight, and expendable upper stage(s) to inject a 500 kg payload in different low Earth orbits.

TL;DR: The results show that the proper filter method and the background image subtraction can effectively eliminate the image noises in frequency domain, which makes it easier to analyze the flow structure.

TL;DR: The Future UK Small Payload Launcher (FSPLUK) as mentioned in this paper is an air launched integrated re-usable first stage vehicle, configured with a flexible internal payload bay from which one or more upper stages are deployed.

TL;DR: In this paper, the authors describe a preferable vehicle classification alongside a brief description of key technologies available on the shelf or under development to address the demand of the small payload market, followed by a discussion on the investigation of the current market and the future forecast; regarding the delivery of small payloads into orbit.

TL;DR: The aim of the system design is to develop a commercially viable launch system for near-term operation, thus emphasis is placed on the efficient use of high TRL technologies and on the commercial potential of the technical design.