Showing papers on "Spacecraft propulsion published in 2017"

Overview of NASA Electrified Aircraft Propulsion Research for Large Subsonic Transports

Abstract: NASA is investing in Electrified Aircraft Propulsion (EAP) research as part of the portfolio to improve the fuel efficiency, emissions, and noise levels in commercial transport aircraft. Turboelectric, partially turboelectric, and hybrid electric propulsion systems are the primary EAP configurations being evaluated for regional jet and larger aircraft. The goal is to show that one or more viable EAP concepts exist for narrow body aircraft and mature tall-pole technologies related to those concepts. A summary of the aircraft system studies, technology development, and facility development is provided. The leading concept for mid-term (2035) introduction of EAP for a single aisle aircraft is a tube and wing, partially turbo electric configuration (STARC-ABL), however other viable configurations exist. Investments are being made to raise the TRL level of light weight, high efficiency motors, generators, and electrical power distribution systems as well as to define the optimal turbine and boundary layer ingestion systems for a mid-term tube and wing configuration. An electric aircraft power system test facility (NEAT) is under construction at NASA Glenn and an electric aircraft control system test facility (HEIST) is under construction at NASA Armstrong. The correct building blocks are in place to have a viable, large plane EAP configuration tested by 2025 leading to entry into service in 2035 if the community chooses to pursue that goal.

Aircraft Propulsion and Gas Turbine Engines

Abstract: Aircraft Propulsion and Gas Turbine Engines, Second Edition builds upon the success of the book’s first edition, with the addition of three major topic areas: Piston Engines with integrated propeller coverage; Pump Technologies; and Rocket Propulsion. The rocket propulsion section extends the text’s coverage so that both Aerospace and Aeronautical topics can be studied and compared. Numerous updates have been made to reflect the latest advances in turbine engines, fuels, and combustion. The text is now divided into three parts, the first two devoted to air breathing engines, and the third covering non-air breathing or rocket engines.

Aero-thermo-chemical characterization of ultra-high-temperature ceramics for aerospace applications

Abstract: Ultra-High-Temperature Ceramic (UHTC) materials, because of their high temperature resistance, are suitable as thermal protection systems for re-entry vehicles or components for space propulsion. Massive UHTC materials are characterized by poor thermal shock resistance, which may be overcome using C or SiC fibers in a UHTC matrix (UHTCMC). The University of Naples “Federico II” has a proven experience in the field of material characterization in high-enthalpy environments. A hypersonic arc-jet facility allows performing tests in simulated atmospheric re-entry conditions. The Aerospace Propulsion Laboratory is employed for testing rocket components in a representative combustion environment. Ad-hoc computational models are developed to characterize the flow field in both facilities and perform thermal analysis of solid samples. Current research programs are related to a new-class of UHTCMC materials, for rocket nozzles and thermal protection systems. The activities include design of the prototypes for the test campaign, numerical simulations and materials characterizations.

Modern Propulsions for Aerospace-A Review

Abstract: A spacecraft propulsion is any method used to accelerate spacecraft and artificial satellites. There are several different methods, each with advantages and disadvantages, spacecraft propulsion being an active area of research. However, most current spacecraft are propelled by forcing a gas exits through the rear of the vehicle at high speed through supersonic nozzle of a rocket engine. All spacecraft are using chemical rockets (fuel or solid fuel) to launch, although some (such as Pegasus missiles and Space Ship One) are using air jet engines in the first step. Most satellites have simple chemical thrusters (often missiles mono) or missiles resistojet to maintain orbit. Soviet bloc satellites have used electric propulsion for decades and the new Western geo-orbital spacecraft begin using electric propulsion for orbit maintenance of north-south. There is a need increasingly of more new propulsion systems, modern, technology-based.

Modern Propulsions for Aerospace-Part II

Abstract: Speaking about a new engine ionic means to speak about a new aircraft. The paper presents in a short time the actual engines ion chambers (called the ion thrusters) and other new ionic motors proposed by the authors. The engine (ionic propulsion unit of ions, that accelerates the positive ions through a potential difference) is approximately ten times more efficient than classic system based on combustion. We can further improve the efficiency of the 10-50 times in the case in which is used the pulses of positive ions accelerated in a cyclotron mounted on the ship; efficiency may increase with ease of a thousand times in the case in which the positive ions will be accelerate in a synchrotron high energy, synchrocyclotron or isochronous cyclotron (1-100 GeV). For this, the great classic synchrotron is reduced to a surface-ring (magnetic core). The future (ionic) engine will have a circular particle binding (energy high or very high speed). Thus we can increase the speed and autonomy of the vessel, using a smaller quantity of fuel. It can be used a radiation synchrotron (synchrotron high intensity), with X-ray or gamma radiation. In this case, will result in a beam engine with the wiring (not an ionic engine), which will use only the power (energy, which may be solar energy, nuclear energy, or a combination) and so we will eliminate the fuel. It is suggested to use a powerful LINAC at the outlet of the synchrotron (especially when one accelerates the electron beam) in order not to lose power by photons of the emission premature. With a new ionic engine practically builds a brand new aircraft that can move through the water and air with the same ease. This new aircraft will be able to expedite directly, without an engine with the additional combustion and without the gravity assistance.

Chemical Rocket Propulsion

Abstract: The first € price and the £ and $ price are net prices, subject to local VAT. Prices indicated with * include VAT for books; the €(D) includes 7% for Germany, the €(A) includes 10% for Austria. Prices indicated with ** include VAT for electronic products; 19% for Germany, 20% for Austria. All prices exclusive of carriage charges. Prices and other details are subject to change without notice. All errors and omissions excepted. L.T. De Luca, T. Shimada, V.P. Sinditskii, M. Calabro (Eds.) Chemical Rocket Propulsion

Three-Dimensional Printing of “Green” Fuels for Low-Cost Small Spacecraft Propulsion Systems

Abstract: This paper details the advantages of employing modern additive manufacturing methods to fabricate hybrid rocket fuels for intrinsically safe and green small spacecraft propulsion systems. Using add...

Verification Firings of End-Burning Type Hybrid Rockets

Abstract: The authors have previously proposed the concept of end-burning-type hybrid rockets, which would use cylindrical fuel grains consisting of an array of many small ports running in the axial directio...

Hall Thruster Development for Japanese Space Propulsion Programs

Abstract: 1)Department of Aeronautics and Astronautics, The University of Tokyo, Tokyo 113–8656, Japan 2)Department of Advanced Energy Engineering Science, Kyushu University, Kasuga, Fukuoka 816–8580, Japan 3)Institute of Space and Astronautical Science, JAXA, Sagamihara, Kanagawa 252–5210, Japan 4)IHI Aerospace Co., Ltd., Tomioka, Gunma 370–2398, Japan 5)Research and Development Directorate, JAXA, Chofu, Tokyo 182–8522, Japan 6)Department of Aerospace Engineering, Tokyo Metropolitan University, Tokyo 191–0065, Japan 7)IHI Corporation, Yokohama, Kanagawa 235–8501, Japan 8)Department of Aeronautics and Astronautics, Osaka Institute of Technology, Osaka 535–8585, Japan

Supersonic plasma beams with controlled speed generated by the alternative low power hybrid ion engine (ALPHIE) for space propulsion

Abstract: The characteristics of supersonic ion beams from the alternative low power hybrid ion engine (ALPHIE) are discussed. This simple concept of a DC powered plasma accelerator that only needs one electron source for both neutral gas ionization and ion beam neutralization is also examined. The plasma production and space charge neutralization processes are thus coupled in this plasma thruster that has a total DC power consumption of below 450 W, and uses xenon or argon gas as a propellant. The operation parameters of the plasma engine are studied in the laboratory in connection with the ion energy distribution function obtained with a retarding-field energy analyzer. The ALPHIE plasma beam expansion produces a mesothermal plasma flow with two-peaked ion energy distribution functions composed of low and high speed ion groups. The characteristic drift velocities of the fast ion groups, in the range 36.6–43.5 Km/s, are controlled by the acceleration voltage. These supersonic speeds are higher than the typical ion...

Prospects of Aluminum Modifications as Energetic Fuels in Chemical Rocket Propulsion

Abstract: The use of metals as high-energy fuels has been for long time a common approach to increase performance of chemical rocket propulsion in general. This effort was initially triggered by theoretical thermochemical considerations, but under real operating conditions, a series of collateral and unforeseen effects occurred, with both positive and negative consequences. After six decades, the use of micron-sized Al is the most common practice at industrial level for solid rocket propulsion in particular. Yet attempts are under way to mitigate some of the most deleterious effects: notably, the two-phase flow losses and slag accumulation taking place in gasdynamic nozzles. In this paper, a range of modified Al powders is discussed, going from nano-sized uncoated to coated Al particles and from chemically to mechanically activated micron-sized Al. These variants are duly characterized and comparatively tested under laboratory burning conditions. Due to page limitations, mainly the class of aluminized composite propellants (ammonium perchlorate/inert binder) and operating conditions often used in space applications are investigated. The reader is cautioned to avoid making generalizations to other formulations and conditions based on this limited dataset. Each of the tested Al variants has its own properties, and implementation in full-scale propulsive systems needs to be carefully evaluated for an overall assessment. The recommended strategy for best results is a dual mode Al mixture, synergistically exploiting each component. Other metal fuels, especially hydrides and boron compounds, are examined as well. New trends, capable of drastically changing the current situation but still in their infancy as of this writing, are briefly discussed at the end of the paper.

Years of Test Complex M11 in Lampoldshausen - Research on Space Propulsion Systems for Tomorrow

Abstract: Basic research activities and thrust chamber oriented technology development activities for rocket and air-breathing (ram-/scramjet) propulsion systems are conducted at the M11 test complex at Lampoldshausen test site. The first part of M11 was erected in 1966. In the 50 years of its existence, important scientific results could be elaborated in the multifarious working areas and have been published in a very large number of publications in journals and on conferences. Today the R&D activities are focussed on the development of thrust chamber processes with advanced and above all green propellants. This publication gives a short overview of the history of the test complex and delivers a short inside into current R&D activities.

Rocket Propulsion Powered Using a Gyrotron

Abstract: This paper presents a review of a beamed energy propulsion rocket, the Microwave Rocket, which produces propulsive thrust from millimeter-wave beams transferred from the ground. The thrust is generated through millimeter-wave discharge driven in a cylindrical thruster. As a high-power millimeter-wave generator, a Gyrotron is promising as the beam source. The salient benefit of Microwave Rockets is the resultant drastic cost reduction of mass transportation into space. We have already conducted launch experiments and have achieved continuous thrust generation under multi-pulse operation. Recently, a long-distance beam transfer system has been developed. Ignition tests have been conducted. The physics of the millimeter-wave discharge remain unclear. Additional studies using experimentation and calculations must be conducted to optimize the thrust generation.

Exploring the Heliogyro’s Orbital Control Capabilities for Solar Sail Halo Orbits

Abstract: Solar sailing is an elegant form of space propulsion that reflects solar photons off a large membrane to produce thrust. Different sail configurations exist, including a traditional fixed polygonal...

Numerical comparison of exhaust plume flow behaviors of small monopropellant and bipropellant thrusters.

Abstract: In general, a space propulsion system has a crucial role in the normal mission operations of a spacecraft. Depending on the types and number of propellants, a monopropellant and a bipropellant thrusters are mostly utilized for low thrust liquid rocket engines. As the plume gas flow exhausted from these small thrusters expands freely in a vacuum space environment along all directions, adverse effects of the plume impingement onto the spacecraft surfaces can dramatically reduce the function and performance of a spacecraft. Thus, the purpose of the present study is to investigate and compare the major differences of the plume gas flow behaviors numerically between the small monopropellant and bipropellant thrusters. To ensure efficient numerical calculations, the whole physical domain was divided into three different subdomains depending on the flow conditions, and then the appropriate numerical methods were combined and applied for each subdomain sequentially. With the present analysis results, the plume gas behaviors including the density, the overall temperature and the separation of the chemical species are compared and discussed between the monopropellant and the bipropellant thrusters. Consequently, the present results are expected to provide useful information on selecting the appropriate propulsion system, which can be very helpful for actual engineers practically during the design process.

Sounding Rocket "HEROS" - A Low-Cost Hybrid Rocket Technology Demonstrator

Abstract: The inherent safety of hybrid rocket propulsion offers some unique advantages com- pared to solid and liquid propellant rocket engines. This makes it especially attractive for space tourism, Micro-launcher and hands-on experiments in the education of students. On November 8th, 2016 at 10:30 a.m. the hybrid sounding rocket HEROS 3 was launched from the ESRANGE Space Center to an apogee altitude of 32,300m (106,000 ft). This set a new altitude record for European student and amateur rocketry and a world altitude record for hybrid rockets built by students. The 7.5m long rocket was using Nitrous Oxide (N2O) and a Paraffin-based fuel to produce 10,000N of thrust. The dry mass of the rocket was only 75 kg thanks to a carbon fibre structure for the most part. The rocket performed the record breaking flight at perfect weather and visibility conditions, reaching a maximum airspeed of 720 m/s and Mach 2.3. The rocket performed a soft landing with two parachutes and can be reused. Flight data and engine performance data are published and analyzed. The flight data shows excellent stability of the rocket. Engine performance data proves very high efficiency and stable combustion as in the ground tests. The subsystem design and verification before the launch is reported. Engine and flight trajectory simulations show very good agreements with the flight data. Furthermore, the overall project, the rocket design, the subsystems as well as the launch campaign are presented here in detail.

Spacecraft propulsion system and method

Abstract: The invention relates to the field of spacecraft propulsion, and more specifically to electrically powered spacecraft propulsion. A spacecraft propulsion system (100) according to the invention includes at least one electrostatic thruster (101) with at least one first electricity consumer, a resistojet (102), a circuit (104) for supplying a propellant fluid, and a circuit (103) for supplying electricity comprising at least one first electricity supply line (131) and a first switch (114-1, 114'-1, 114"-1) making it possible to choose between connecting said first electricity supply line (131) to the resistojet (102) and connecting said first electricity supply line (131) to said first electricity consumer of the electrostatic thruster (101). This system thus allows the application of a spacecraft propulsion method including a switching step for selecting a first propulsion mode, in which the resistojet (102) is activated, or a second propulsion mode, in which the electrostatic thruster (101) is activated.

Metasurface solar sail

Abstract: Solar sails are spatial sails using radiation pressure as a spacecraft propulsion method. This technology is so far limited to repulsive forces. We propose a metasurface solar sail system that is able to produce not only repulsive forces but also attractive, lateral and rotational forces. The forces acting on the metasurface sail are produced by the light of a star or may be controlled by changing the polarization or wavelength of a laser beam. Here, we only present the field configurations corresponding to those four different forces. The design of the metasurfaces will be discussed at the conference.

Transient propagation dynamics of flowing plasmas accelerated by radio-frequency electric fields

Abstract: Flowing plasmas are of significant interest due to their role in astrophysical phenomena and potential applications in magnetic-confined fusion and spacecraft propulsion The acceleration of a charge-neutral plasma beam using the radio-frequency self-bias concept could be particularly useful for the development of neutralizer-free propulsion sources However, the mechanisms that lead to space-charge compensation of the exhaust beam are unclear Here, we spatially and temporally resolve the propagation of electrons in an accelerated plasma beam that is generated using the self-bias concept with phase-resolved optical emission spectroscopy When combined with measurements of the extraction-grid voltage, ion and electron currents, and plasma potential, the pulsed-periodic propagation of electrons during the interval of sheath collapse at the grids is found to enable the compensation of space charge

Hybrid Propulsion Technology Development in Japan for Economic Space Launch

Abstract: The demand for the economic and dedicated space launchers for vast amount of lightweight, so-called nano-/microsatellites, is now growing rapidly. There is a strong rationale for the usage of the hybrid propulsion for economic space launch as suggested by the assessment conducted here. A typical concept of development of such an economic three-stage launcher, in which clustering unit hybrid rocket engines are employed, is described with a development scenario. Thanks to the benefits of hybrid rocket propulsion, assuring and safe, economic launcher dedicated to lightweight satellites can be developed with a reasonable amount of quality assurance and quality control actions being taken in all aspects of development such as raw material, production, transportation, storage, and operation. By applying a multi-objective optimization technique for such a launch system, examples of possible launch systems are obtained for a typical mission scenario for the launch of lightweight satellites. Furthermore, some important technologies that contribute strongly to economic space launch by hybrid propulsion are described. They are the behavior of fuel regression rate, the swirling-oxidizer-flow-type hybrid rocket, the liquid oxygen vaporization, the multi-section swirl injection, the low-temperature melting point thermoplastic fuel, the thrust and O/F simultaneous control by altering-intensity swirl-oxidizer-flow-type (A-SOFT) hybrid, the numerical simulations of the internal ballistics, and so on.

Development of a 13 kW Hall Thruster Propulsion System Performance Model for AEPS

Abstract: The Advanced Electric Propulsion System (AEPS) program will develop a flight 13kW Hall thruster propulsion system based on NASA’s HERMeS thruster. The AEPS system includes the Hall Thruster (HT), the Power Processing Unit (PPU) and the Xenon Flow Controller (XFC). These three primary components must operate together to ensure that the system generates the required combinations of thrust and specific impulse at the required system efficiencies for the desired system lifetime. At the highest level, the AEPS system will be integrated into the spacecraft and will receive power, propellant, and commands from the spacecraft. Power and propellant flow rates will be determined by the throttle set points commanded by the spacecraft. Within the system, the major control loop is between the mass flow rate and thruster current, with time-dependencies required to handle all expected transients, and additional, much slower interactions between the thruster and cathode temperatures, flow controller and PPU. The internal system interactions generally occur on shorter timescales than the spacecraft interactions, though coordination with the spacecraft commands and telemetry will be at the higher frequency. The AEPS system performance model is designed to account for all these interactions in a way that allows evaluation of the sensitivity of the system to expected changes over the planned mission as well as to assess the impacts of normal component and assembly variability during the production phase of the program. This paper describes the initial efforts toward the system performance model development, correlation to NASA test data, and how the model will be used to evaluate the critical internal and external interactions. The results will ensure the component requirements do not unnecessarily drive the system cost or overly constrain the development