Development of Ionic Liquid Multi mode Spacecraft Micropropulsion Systems

Produk Detail:
  • Author : Steven Paul Berg
  • Publisher : Unknown
  • Pages : 149 pages
  • ISBN :
  • Rating : /5 from reviews
CLICK HERE TO GET THIS BOOK >>>Development of Ionic Liquid Multi mode Spacecraft Micropropulsion Systems

Download or Read online Development of Ionic Liquid Multi mode Spacecraft Micropropulsion Systems full in PDF, ePub and kindle. this book written by Steven Paul Berg and published by Unknown which was released on 11 May 2021 with total page 149 pages. We cannot guarantee that Development of Ionic Liquid Multi mode Spacecraft Micropropulsion Systems book is available in the library, click Get Book button and read full online book in your kindle, tablet, IPAD, PC or mobile whenever and wherever You Like. "This dissertation presents work on development of multi-mode specific spacecraft propulsion systems. Specifically, this work attempts to realize a single propellant capable of both chemical monopropellant and electric electrospray rocket propulsion, develop methods to characterize multi-mode propulsion system performance, and realize a system capable of both monopropellant and electrospray propulsion for a small spacecraft. Selection criteria for ionic liquid propellants capable of both monopropellant and electrospray propulsion are developed. These are based on desired physical properties and performance considering use in both propulsive modes. From these insights, a monopropellant mixture of 1-ethyl-3-methylimidazolium ethyl sulfate and hydroxylammonium nitrate is selected and synthesized. Multi-mode spacecraft micropropulsion systems which include a high-thrust chemical mode and high-specific impulse electric mode are assessed. Due to the combination of a common propellant for both propulsive modes, low inert mass, and high electric thrust, the monopropellant/electrospray system has the highest mission capability in terms of delta-V for missions lasting shorter than 150 days. The ionic liquid monopropellant mixture is tested for decomposition on heated platinum, rhenium, and titanium surfaces. It was found that the propellant decomposes at 165 °C on titanium, which is the decomposition temperature of HAN, and 85 °C on platinum. Arrhenius-type reaction rate parameters were calculated from the results and used to develop thruster models. The [Emim] [EtSO4]-HAN propellant mixture is tested in a capillary electrospray emitter and exhibits stable electrospray emission at a nominal extraction voltage of 3400 V. The highest specific impulse attained in these experiments was 412 seconds; however, this could be improved with a more robust feed system design. This data, along with data from the monopropellant decomposition experiment is used to design a multi-mode micropropulsion system using a common propellant and common thruster geometry. This system is capable of ~20-40% greater delta-V capability at a given mission duration compared to a system utilizing separate, state-of-the-art monopropellant and electrospray thrusters"--Abstract, page iv.

Development of Ionic Liquid Multi mode Spacecraft Micropropulsion Systems

Development of Ionic Liquid Multi mode Spacecraft Micropropulsion Systems
  • Author : Steven Paul Berg
  • Publisher : Unknown
  • Release : 11 May 2021
GET THIS BOOK Development of Ionic Liquid Multi mode Spacecraft Micropropulsion Systems

"This dissertation presents work on development of multi-mode specific spacecraft propulsion systems. Specifically, this work attempts to realize a single propellant capable of both chemical monopropellant and electric electrospray rocket propulsion, develop methods to characterize multi-mode propulsion system performance, and realize a system capable of both monopropellant and electrospray propulsion for a small spacecraft. Selection criteria for ionic liquid propellants capable of both monopropellant and electrospray propulsion are developed. These are based on desired physical properties and performance considering use

The Effect of Temperature on the Structure of Colloid Thrusters Beams

The Effect of Temperature on the Structure of Colloid Thrusters Beams
  • Author : Maria Pau Bravo
  • Publisher : Unknown
  • Release : 11 May 2021
GET THIS BOOK The Effect of Temperature on the Structure of Colloid Thrusters Beams

This work investigates the effect of the temperature on the structure of electrospray beams. Electrospraying is a technique used to atomize charged liquids. From the different operational modes, the cone-jet mode is characterized by its stability [1] and is used in several applications as mass spectrometry [2], nanodroplets sputtering [3] or space propulsion (colloid thrusters). Colloid thrusters are electrostatic accelerators of charged particles. The very low thrust that a single needle provides can be used for precision spacecraft positioning and drag cancellation missions.

Nanosatellites

Nanosatellites
  • Author : Rogerio Atem de Carvalho,Jaime Estela,Martin Langer
  • Publisher : John Wiley & Sons
  • Release : 16 March 2020
GET THIS BOOK Nanosatellites

Nanosatellites: Space and Ground Technologies, Operations and Economics Rogerio Atem de Carvalho, Instituto Federal Fluminense, Brazil Jaime Estela, Spectrum Aerospace Group, Germany and Peru Martin Langer, Technical University of Munich, Germany Covering the latest research on nanosatellites Nanosatellites: Space and Ground Technologies, Operations and Economics comprehensively presents the latest research on the fast-developing area of nanosatellites. Divided into three distinct sections, the book begins with a brief history of nanosatellites and introduces nanosatellites technologies and payloads, also explaining how these

Micro Newton Thruster Development

Micro Newton Thruster Development
  • Author : Franz Georg Hey
  • Publisher : Springer
  • Release : 01 March 2018
GET THIS BOOK Micro Newton Thruster Development

Franz Georg Hey summarises the development and testing of a micro-Newton thrust balance, as well as the downscaling of a High Efficiency Multistage Plasma Thruster to micro-Newton thrust levels. The balance is tailored to fully characterise thruster candidates for the space based gravitational wave detector LISA. Thus, thrust noise measurements in sub-micro-Newton regime can be performed in the overall LISA bandwidth. The downscaled thruster can be operated down to serval tens of micro-Newton with a comparably high specific impulse. About

Feasibility Study of Laser fabricated Micro needles as an Electrospray Thruster

Feasibility Study of Laser fabricated Micro needles as an Electrospray Thruster
  • Author : Andrew Joseph Broadbent
  • Publisher : Unknown
  • Release : 11 May 2021
GET THIS BOOK Feasibility Study of Laser fabricated Micro needles as an Electrospray Thruster

Capable of carrying small-scale instruments, micro-satellites, often called CubeSats for their shape, provide an excellent platform for a variety of educational and research missions. However, once placed in orbit satellites experience small amounts of drag that slow the craft down, and deteriorate its orbit over time. The addition of a propulsion system will allow a CubeSat to correct and maintain orbit, as well as perform other maneuvers. Due to their size and power requirements, CubeSats cannot accommodate conventional propulsion methods.

Encyclopedia of Bohemian and Czech American Biography

Encyclopedia of Bohemian and Czech American Biography
  • Author : Miloslav Rechcigl Jr.
  • Publisher : AuthorHouse
  • Release : 10 November 2016
GET THIS BOOK Encyclopedia of Bohemian and Czech American Biography

As the Czech ambassador to the United States, H. E. Petr Gandalovic noted in his foreword to this book that Mla Rechcgl has written a monumental work representing a culmination of his life achievement as a historian of Czech America. The Encyclopedia of Bohemian and Czech American Biography is a unique and unparalleled publication. The enormity of this undertaking is reflected in the fact that it covers a universe, starting a few decades after the discovery of the New World,

Spacecraft Systems Engineering

Spacecraft Systems Engineering
  • Author : Peter Fortescue,John Stark,Graham Swinerd
  • Publisher : Wiley
  • Release : 11 May 2021
GET THIS BOOK Spacecraft Systems Engineering

Following on from the hugely successful previous editions, the third edition of Spacecraft Systems Engineering incorporates the most recent technological advances in spacecraft and satellite engineering. With emphasis on recent developments in space activities, this new edition has been completely revised. Every chapter has been updated and rewritten by an expert engineer in the field, with emphasis on the bus rather than the payload. Encompassing the fundamentals of spacecraft engineering, the book begins with front-end system-level issues, such as environment,

Material and Fabrication Developments in the Ion electrospray Propulsion System

Material and Fabrication Developments in the Ion electrospray Propulsion System
  • Author : Jonathan V. MacArthur
  • Publisher : Unknown
  • Release : 11 May 2021
GET THIS BOOK Material and Fabrication Developments in the Ion electrospray Propulsion System

In this thesis, new materials, microfluidic control devices, and fabrication techniques were developed in support of the ion electrospray propulsion system (iEPS) developed by MIT’s Space Propulsion Lab. MEMS fabrication techniques are reworked to increase yield reliability of the thruster frames. The focus of this work is on propellant management, increasing thrust density, system robustness, and reducing cost of thruster production. Altered fabrication process steps have led to reliable 100 percent yields. A large focus of improving iEPS thrusters is