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International Space Station

This paper presents the conceptual design and performance analysis of a partially reusable space launch vehicle for small payloads. The system 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. The space access vehicle is designed to be air-launched from a modified aircraft carrier. 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. The vehicle design are analysed using a multi-disciplinary design optimisation approach to evaluate the performance, operational capabilities and design trade-offs.

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Vehicle and mission design of a future small payload launcher

Conceptual design analysis for a two-stage-to-orbit semi-reusable launch system for small satellites

The French Space Agency (Centre National d'Etudes Spatiales-CNES), the UK Space Agency (UKSA), Reaction Engines Limited (REL) and the French Aerospace Lab (Office National d'Etudes et de Recherches Aerospatiales-ONERA) share a common interest for future space launch architectures and technologies. Preliminary results of a joint study are presented in this paper with the main objective of assessing and quantifying the potential advantages and benefits of air-breathing propulsion technology developed by REL named SABRE (Synergetic Air-Breathing Rocket Engine) for future launch architectures. In that purpose, a conceptual study of two alternative Two-Stage-To-Orbit (TSTO) vehicles is carried out using the SABRE air-breathing rocket engine and a LOx/CH4 rocket engine (for the second stage) for the injection of a 15t payload into low Earth orbit. Different analyses are carried out using a coupled multidisciplinary process involving propulsion, aerodynamics, sizing and trajectory optimizations. Some key influential parameters and intricate behaviors are analyzed through sensitivity to the stage separation conditions. As a result, these analyses provide insight into technological requirements to achieve the target mission using these types of advanced propulsion technologies.

https://hal.archives-ouvertes.fr/hal-02901387/document

Conceptual design of a Two-Stage-To-Orbit vehicle using SABRE engines

NASA successfully kicked off a series of tests Sept. 30 to qualify Orion’s parachute system for flights with astronauts.

NASA Begins Tests to Qualify Orion Parachutes for Mission with Crew

Miniaturisation of satellite componentry, increasingly capable small sensors and substantial increases in processing capacity and transmission bandwidth are driving rapid growth in small payload development and consequential launch demand. The advent of horizontal take-off spaceports opens the door for a new generation of small payload launch systems that will fulfil this demand. However, the key to a launch system's success is its ability to provide a return on the substantial costs of development while delivering pricing levels commensurate with the needs of launch customers. Therefore, commercially led design approaches are needed to refine and optimise the design of the new small payload launch systems required. This approach was embodied in an ongoing UKSA funded NSTP2 project titled Future UK Small Payload Launcher (FSPLUK). The approach is first founded upon a bespoke and specific market assessment. This characterises, segments and quantifies the commercial opportunity and establishes principal desired system performance requirements. An assessment of available technologies at differing TRLs permits initial vehicle configuration options to be developed and technically assessed. Technically viable options are then assessed in terms of commercial viability with the best advanced into more detailed technical assessment and system optimisation. The resultant vehicles are again tested for commercial viability and, if successful, emerge as recommended development avenues. Using these methods, it has been possible to iterate design concepts from apparently simple yet economically sub-optimised stacked launcher systems through several design iterations to a resultant highly flexible and economically efficient conceptual design. The key finding relates to the inter-relationship between payload flexibility, in permitting maximised flight rates from a reasonably complex but highly reusable first stage design, and low disposable upper stage unit cost. This has driven the resultant system to feature 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. This configuration maximises commercial utility and reusability. The resultant high flight rate allows development costs to be efficiently amortised with minimised direct launch costs. The configuration therefore meets low cost per kg price targets while delivering a positive return on development expenditure over life. It also provides a flight proven vehicle platform with available internal real-estate for application as a hypersonic air test platform for new propulsion systems, such as SABRE. The commercially led approach has created the foundation for viable and economically justifiable development.

A commercially driven design approach to UK future small payload launch systems

This paper describes 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. This is followed by a discussion on the investigation of the current market and the future forecast; regarding the delivery of small payloads into orbit.

Travis Fawcett

Papers

A commercially driven design approach to UK future small payload launch systems

How to launch small payloads? Evaluation of current and future small payload launch systems