Electrothermal microthruster

Electrothermal propulsion can be seen as an intermediate concept between electrical and chemical propulsion. Propellant heating typically happens by means of a resistance (resistojet) or an electrical discharge (arcjet). For the extremely miniaturized applications that will be discussed in this chapter, resistojets are by far the most...

Bi-modal solar thermal propulsion and power system: Modelling and optimisation for the next-generation of small satellites

Exploring and utilising space to benefit humankind is undeniably a costly venture where the higher the mass of the satellite, the higher the cost to launch. However, the rewards of space-related achievements are indisputable. These achievements range from increasing our understanding of the universe using satellites, such as the Hubble Space...

Design and characterisation of a bi-modal solar thermal propulsion and power system for small satellites

Small satellites with increased capabilities in terms of power and propulsion are being demanded for future missions. This paper addresses an alternative bi-modal solution which consists of a solar thermal propulsion system coupled with a micro-Organic Rankine Cycle system, to co-generate thrust and electrical power. Current literature on bi...

Solar energy harvesting on-board small satellites

Small satellites are receiving increased recognition in the space domain due to their reduced associated launch costs and shorter lead time when compared to larger satellites. However, this advantage is often at the expense of mission capabilities, such as available electrical power and propulsion. A possible solution is to shift from the...

Design of a Solar Thermal Propulsion and Power System for Mini-satellite Lunar Orbit Insertion

Small satellites with increased capabilities in terms of power and propulsion are being demanded for future missions. This paper proposes a possible solution which is the design of a novel integrated solar thermal system that co-generates propulsion and power on-board mini satellites. The system consists of a solar thermal propulsion system ...

Feasibility of an On-Board Micro-ORC System for Small Satellites

Small satellites are receiving increased recognition in the space domain due to their reduced associated launch costs and their shorter lead time when compared to larger satellites. However, this advantage is often at the expense of mission capabilities, such as available electrical power and propulsion. A possible solution is to change from the...

Conceptual design and numerical validation of a composite monocoque solar passenger vehicle chassis

The concept of the composite monocoque chassis has been implemented in many vehicle designs; however, there is limited open literature defining the process of simulating a composite monocoque chassis. The purpose of this research is to develop a composite monocoque chassis by analysing its structural integrity through an iterative finite...