Alexander Reissner's scientific contributions

Publications (13)

Conference Paper
Full-text available
The in-orbit demonstration of an ENPULSION NANO propulsion system in 2018 marked the first liquid metal field emission electric propulsion system tested in space, and the successful introduction of the ENPULSION NANO. In the four years since then, this propulsion system was successfully industrialized and 136 systems have flown on 61 different spac...
Conference Paper
Full-text available
Space propulsion systems undergo thorough ground testing before being deployed in space. We report the results of a functional verification and performance characterisation test campaign of an integrated electric propulsion system for cubesats and microsats with purely electric thrust vectoring capability and no moving parts. Visualisations of the...
Conference Paper
View Video Presentation: https://doi.org/10.2514/6.2021-3420.vid The ENPULSION NANO and the ENPULSION MICRO are both based on liquid metal Field Emission Electric Propulsion (FEEP) principle, producing thrust by electrostatically accelerating previously extracted and ionized propellant to high exhaust velocity. The Indium FEEP emitter is based on p...
Conference Paper
Full-text available
The IFM Nano Thruster is a high specific impulse liquid metal Field Emission Electric Propulsion (FEEP) system that has been flown on multiple space missions ranging from 3U Cubesats to 100 kg class satellites. The core component of the thruster is a crown-shaped porous metal ion emitter featuring 28 ion emission sites, with propellant supplied pas...
Conference Paper
Full-text available
With the rising market in small satellite constellations and emerging New Space companies , the demand in propulsion systems for Cubesats and small satellites grew rapidly in recent years. Due to its compact design, its versatile operation, and its plug-and-play character, the IFM Nano Thruster was and is an electric propulsion system advantageousl...
Preprint
Full-text available
The increase of CubeSat missions with energy demanding payloads and the ongoing miniaturization of electric components lead to growing thermal challenges in those standardized small satellites. For upcoming commercial and scientific missions, it is important to overcome these challenges and to provide the necessary thermal conditions for demanding...
Article
The IFM Nano Thruster, which consists of a porous tungsten crown ion-emitter to provide thrust in the range of 10 µN to 1 mN at 2000–5000 s ISP, has been tested on a µN thrust balance that has previously been verified at the ESA Propulsion Laboratories. A comprehensive assessment of the thrust performance has been complemented by measurements of th...
Conference Paper
Full-text available
The IFM Nano Thruster is a variable specific impulse electrostatic thruster based on Field Emission Electric Propulsion (FEEP), in which a liquid propellant is electrostatically extracted and accelerated to high exhaust velocity. The core element of this propulsion technology is a passively fed, porous ion emitter consisting of 28 sharp emitter tip...

Citations

... A recent keen interest in novel electric propulsion technologies stems from an increasing number of small satellites being deployed for plural applications [1][2][3][4][5]. Simple and compact thrusters might enable in-space maneuvering of such small spacecrafts [6]. ...
... After launch in Dec 2018, the first propulsion system based on liquid metal Field Emission Electric Propulsion (FEEP) was successfully demonstrated in orbit in 2019 in an IOD conducted together with FOTEC [1,2,3]. Since then, 135 additional ENPULSION NANO systems (formerly IFM Nano Thruster) were launched. ...
... 287,288 Since this is rather difficult to realize with externally wetted electrodes and difficult with internally wetted electrodes (see below), the first commercially successful thrusters were based on porous emitter materials, brought into shape by conventional machining techniques. Prominent examples for LMISs are the crown emitters from ENPULSION (Austria), 276,289 which use liquid indium as the propellant, and ILIS propulsion systems have been brought to the space market by BUSEK 277 (US). For ILIS systems, the activities of Alta in Europe with its Slit-FEEP system should also be mentioned. ...
... If deployable radiator panels are used, it is very important to ensure that the thermal conductivity is higher for the hinges used. Flexible thermal straps along with proper mechanical hinges, which have variable bending angles, can be used to deploy radiators [33]. Flexible thermal straps can be considered for thermal connection between the heat dissipating element and the deployable radiator. ...
... The nude Faraday probe would therefore be suitable for low-energetic beams with low density, as it provides a large collector area with high sensitivity [1]. In 2018 FOTEC developed a segmented system consisting of 252 nude Faraday probes to analyse the relative current density distribution of FEEP thrusters [10]. Following, extensions of the standard form of the Faraday probe are presented. ...
... Early 2018 the first spacecraft equipped with an IFM Nano Thruster was launched. The thruster has been developed by the research company FOTEC and is commercialised by the space tech company EN-PULSION [1,2]. Since then, over 80 IFM Nano Thrusters have been brought into space [3] and the need for electric propulsion constantly increases [4]. ...
... Scalability of satellite and propulsion technologies allows for large constellation architectures for a variety of applications, including high temporal resolution earth observation and telecommunication network applications. One of the technologies investigated to fill the current need for compact, high performing propulsion is liquid metal FEEP propulsion [5], [6], [7], which allows for high specific impulse due to the electrostatic acceleration principle [8] and high total impulse due to the high density of the propellant. Liquid metal indium sources have been developed for over 25 years at the FOTEC (former Austrian Institute of Technology) and have gained considerable space heritage [9]. ...
... These applications require short and repeatable startups for fine control, compared to systems for orbit raising which are generally more concerned with performance and thrust over a longer firing [11], [78]. The time to reach steady state operation is important for these applications, and is defined here as 90 , or the time between the actuation of the system and the internal conditions reaching 90 % of the steady state value [113]. 42 ...
... However, in this case an electrical propulsion solution would be more suited from the service lifetime standpoint. A compact solution like that of the Enpulsion R 3 could deliver 10 times the delta-v in the same form-factor [95], leading to a comparable lifetime to that of ICEYE-X1 or Planet Doves. ...
... A new type of FEEP, delivering ∼mN level thrust, that utilises an Indium crown emitter with porous needles has been developed at FOTEC, Austria [112,113]. It was further developed and commercialised as IFM Nano Thruster by Enpulsion in Austria [114]. ...