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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

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

This paper presents a multi-objective trajectory optimisation under uncertainty for the ascent of a two-stage, semi-reusable space launch system. Using Orbital Access’ Orbital 500- R launcher as a test case, robust multi-disciplinary design optimisation is used to analyse the trade-offs with both the vehicle and system design, and operation. An area of focus is on the predicted performance and its impact on the design and planned mission scenarios. The atmospheric model uncertainties are quantified for the atmospheric surrogate model and integrated into the optimal control solver MODHOC, extended by the addition of an unscented transformation to handle the uncertainties. A multi-objective optimisation under uncertainty is run, examining the Pareto-optimal sets for the ascent trajectory and vehicle design.

/pdf/robust-trajectory-optimisation-of-a-tsto-spaceplane-using-3vf57q7cu3.pdf

Robust trajectory optimisation of a TSTO spaceplane using uncertainty-based atmospheric models

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.

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

The Orbital 500R is a commercial semi-reusable, two-stage launch system under development by Orbital Access. The focus of this paper is a numerical aerodynamic analysis of the reusable first stage spaceplane, capable of powered and glided flight. The vehicle is intended to release expendable upper stage(s) to inject 500-kilogram of payload into low Earth orbit. Ejection of the upper stage(s) is expected to be above 85-kilometres, after which the first stage spaceplane will perform re-entry and landing. Toolset validation and the establishment of best practice is an integral aspect of assessing and optimising system performance and controllability. Steps have been taken to progress this, related to the use of Fluid Gravity Engineering Navier-Stokes solver, ANITA. The validation activities were focused around the characterisation of the aerodynamics of two wing-body experimental models, tested across a range of angles of attack at Mach 4.0 and 8.2 respectively. The results have provided a sufficient level of confidence in the use of ANITA to assess the aerodynamic performance of spaceplane wing-body configurations for supersonic and hypersonic flow regimes. A computational assessment of the vehicle's aerodynamics has been performed by means of both engineering-based tools and Navier-Stokes CFD computations. Lessons learned from the validation activities fed into the use of ANITA to characterise the vehicle's aerodynamics from Mach 3.0 and above. The lift and drag characteristics of the vehicle were found to be very comparable to those documented for the X-34 reusable launch vehicle from Mach 2.0 up to Mach 6.0. Furthermore, strong code-to-code agreement was observed with the SU2 and ANSYS-Fluent Navier-Stokes solvers for aerodynamic characteristics at Mach 3.0.

Kostantinos Kontis

Papers

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

Aerodynamic database development for a future reusable space launch vehicle, the Orbital 500R