High accuracy GNSS-based on-board orbit determination and prediction methods for tracking software in satellite laser communications

Laser communication provides numerous benefits over typical Radio Frequency communication, such as lower power, not occupying regulated frequency bands, possibilities for much higher data rates and resistance to jamming. Combined with satellite constellations, Laser Inter-satellite Links (LISL) can enable global connectivity. However, satellites...

In-orbit Refuelling with Hydrogen Peroxide: An Architecture and Transfer Mechanism

The current state of in-orbit refuelling involves launching propellant from the Earth’s surface in a single use refuelling craft, often to transfer hydrazine to the customer. This method is a logical first step however this architecture is not reusable, and it centres around a toxic and carcinogenic propellant. An architecture is proposed where...

Chemical propulsion system design for autonomous Mars CubeSat mission

Interplanetary CubeSat missions enable low-cost exploration missions, in which the design of a primary propulsion system becomes crucial. Emphasis is put on an autonomous Mars mission starting from a parking orbit around Earth: chemical propulsion systems are characterized by high thrust levels and allow fast Earth escape manoeuvres. In recent...

Modelling of electrode-plasma interactions in Pulsed Plasma Thrusters

Electric propulsion is generally characterized by higher specific impulse than traditional chemical rockets, which gives them propellant saving benefits. These have been applied in deep-space missions and micro-satellites. A Pulsed Plasma Thruster consists of two electrodes around a block of teflon. A pulsed discharge ablates the teflon and...

Aerodynamic Design and Analysis of a Two Stage to Orbit Winged semi-Reusable Launching Vehicle

The commercialization of the space industry has led to a reduction in size and weight of satellites and launching vehicles, which have effectively reduced the cost of space services. The costs of launching payloads to space can be significantly reduced when the launching vehicles are reusable. The two-stage-to-orbit system with a winged,...

Preliminary Design of a Small Hydrogen Peroxide Cooled Thrust Chamber for Additive Manufacturing

As a part of a <i>Future Launcher Preparatory Programme</i> contract issued by the European Space Agency, the aerospace startup company Dawn Aerospace is developing an integral, additive manufactured (AM), liquid rocket engine. This 2.5 kN class engine is propelled by the storable propellants 90% hydrogen peroxide and kerosene and used in the...

Novel and Green Hypergolic Bi- Propellant System for Propulsion Application

Some propellants currently used in space propulsion have the disadvantage of being dangerous to humans and the environment. A wellknown example of this are hydrazine and its derivatives which are toxic, corrosive, and carcinogenic. These disadvantages have led to a search for less hazardous storable liquid propellants, often referred to as green...

The design and testing of an injector for anadvanced hypergolic dual-mode propulsionsystem

An important topic in the field of rocket propulsion is the development of a new green advanced hypergolic rocket propulsion system. The current hypergolic propellants have one large drawback, namely the toxic properties. The injector has a crucial role in the performance of a liquid engine. Therefore, the next step in the development of this...

Initial characterization of the Alternative Low Power Hybrid Ion Engine (ALPHIE) plume

This report describes the work performed on the experimental setup and initial characterization of the Alternative Low Power Hybrid Ion Engine (ALPHIE) plume performed at the Universidad Politécnica de Madrid (UPM) Plasma Laboratory. First, a general background of plasma thrusters is presented, followed by a review of relevant plasma parameters...