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Development of a solar thermal thruster system
Also a demonstration solar thermal thruster has been developed and tested at different mass flow rates to verify the model. These tests have been performed using the Delft Aerospace Rocket Test Stand. Measurement parameters included thrust, propellant mass ...
Integrated study on the comprehensive magnetic-field configuration performance in the 150 kW superconducting magnetoplasmadynamic thruster …
Integrated study on the comprehensive magnetic-field ...
High Power Ion Thruster Performance
where D is the thruster beam diameter in meters and R is the ratio of net ion accelerating voltage (Vb) to the total ion accelerating voltage (Vt) and can be varied from about 0.2 to 0.9. The upper limit for R of about 0.9 is determined by the minimum value of the magnitude of the negative voltage on ...
OMNIVOROUS SOLAR THERMAL THRUSTER, COOLING SYSTEMS, AND THERMAL …
The solar thermal thruster is further configured to use a plurality of different propellant types, ... Increasing flow through downstream valves (e.g., the valve 115)—for example, by opening more of them, or opening them to a larger degree—while simultaneously (e ...
Ion Thrusters – What They Are And How They Work
Electrostatic and electromagnetic thrusters are the two primary forms of ion propulsion, of which electrostatic thrusters are most commonly used. (The upcoming section provides a detailed explanation of exactly how an …
NASA Facts
National Aeronautics and Space Administration NA S A acts Ion Propulsion Ion thrusters are being designed for a wide variety of missions—from keeping communications satellites in the proper position (station-keeping) to pro-pelling spacecraft throughout our solar
Multi-plume flow simulation of small bipropellant thrusters using …
To distinguish two different flow regions, the LAE nozzle exit plane was chosen as the breakdown face between the continuum flow and the rarefied flow domains, and this assumption is suitable for numerous rocket …
13kW Advanced Electric Propulsion Flight System Development …
The AEPS System is an EP string that consists of a magnetically shielded Hall thruster, a Power Processing Unit (PPU), a Xenon Flow Controller (XFC), and associated harnessing. The PPU receives up to 13.5 kW of power to control the thruster output and
Fundamentals of Electric Propulsion: Ion and Hall Thrusters
Fundamentals of Electric Propulsion: Ion and Hall Thrusters
4.0 In-Space Propulsion
The bus includes ExoTerra''s Halo thruster, xenon flow control system (XFC), power processing unit (PPU), and deployable solar arrays. The Courier spacecraft provides up to 1 km/s of delta-v, while hosting a 2U, 4 kg payload.
Solar electric propulsion
Solar electric propulsion (SEP) refers to the combination of solar cells and electric thrusters to propel a spacecraft through outer space. [1] This technology has been …
Solar Thermal Propulsion at MSFC
Solar Thermal Upper Stage •30-day orbit transfer of 1000 lbs payload from low earth orbit to geosynchronous •Allows greater initial mass in low earth orbit than traditional chemical upperstages •Future use as orbital maneuvering vehicle for satellites •Design
Ion Thrusters – What They Are And How They Work
This means that, even though they are not capable of generating the high amount of thrust chemical rockets do, ion-thruster-powered spacecraft can achieve very high velocities by continuously firing for extended periods …
Fluid-Solid Coupled Simulation of a Novel Platelet Heat Exchanger Used in Solar Thermal Thruster …
Coupled Simulation of a Novel Platelet Heat Exchanger Used in Solar Thermal Thruster ... the heat transfer and flow field of the platelet passage.The simulation result shows that the propellant ...
Fundamentals of Electric Propulsion: Ion and Hall Thrusters
thruster performance and significantly extend thruster life for applications in deep-space propulsion and satellite station-keeping requires a much deeper understanding of the …
NASA, Aerojet Rocketdyne Put Gateway Thruster System to the …
NASA, Aerojet Rocketdyne Put Gateway Thruster System ...
A Remarkable New Thruster Could Achieve Escape …
A Remarkable New Thruster Could Achieve Escape ...
ESA Science & Technology
Xenon flow control unit, which modulates the mass flow rate of gas entering the thruster Propellant storage tank with a volume of 49 litres, capable of storing 82 kilograms of xenon at a pressure of 150 bar Thruster orientation mechanism, to …
Comparison study of exhaust plume impingement effects of small mono
A space propulsion system is important for the normal mission operations of a spacecraft by adjusting its attitude and maneuver. Generally, a mono- and a bipropellant thruster have been mainly used for low thrust liquid rocket engines. But as the plume gas expelled from these small thrusters diffuses freely in a vacuum space along all …
Performance characterisation of MPD thrusters
In a thermal thruster, propellant is heated by solar or nuclear energy. In both arcjet and thermal thruster, the propellant is expelled through a nozzle. We describe hydrogen resources in the ...
Gridded Ion Thrusters (NEXT-C) | Glenn Research …
NASA''s Evolutionary Xenon Thruster (NEXT) is a gridded-ion thruster. In an ion thruster, ions are accelerated by electrostatic …
Overview of NASA''s Solar Electric Propulsion Project
High-power solar electric propulsion is one of the key technologies that has been prioritized because of its significant exploration benefits, specifically, for missions …
Zendure SolarFlow Balkonkraftwerk 800W mit Speicher Kaufen
Zendure SolarFlow Balkonkraftwerk 800W mit Speicher ...
Thirty percent conversion efficiency from radiofrequency power to ...
The presently reported thruster efficiency is the highest to date in this type of thruster called the helicon thruster; the present results would lead to a new …
A Remarkable New Thruster Could Achieve Escape …
The team essentially miniaturized the high-power solar electric technologies that will make that lunar mission possible into a package that could provide thrust for …
10N, 200N, 400N
10N Bi-Propellant Thruster Key Technical Characteristics Thrust Nominal 10 N (2.2 lbf) Thrust Range 6.0 … 12.5 N Specifi c Impulse at Nominal Point 292 s Flow Rate Nominal 3.50 g/s Flow Rate Range 2.30 … 4.20 g/s Mixture Ratio Nominal 1.60 … 1.65 Mixture
1 N Monopropellant Hydrazine Thruster
Propellant supply to the thruster is provided by a two stage flow control valve comprising two identical monostable, normally closed valves placed in series within a single housing. Additionally each thruster is equipped with an internal redundant catalyst bed heater and with thermal insulation to guarantee optimum start up.
4.0 In-Space Propulsion
The Aurora propulsion system consists of a thruster, cathode, power processing unit, propellant flow controller, and cable harness. The system will be used for …
Direct Simulation Monte Carlo Simulation of the Effect of Needle Valve Structures on the Rarefied Flow of Cold Gas Thrusters
The needle valve, serving as the flow control unit of the thruster system, is a crucial component of the entire thruster. Its performance directly impacts the flow state of the rarefied gas in the micro-nozzle structure of the cold gas micro-thruster, thereby exerting a significant influence on the high precision and stability of the propulsion system …
NEXT Overview facts
National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio 44135 MA-2017 11-1-GRC Pub NEXT-C The NEXT-C Project The NASA''s Evolutionary Xenon Thruster – Commercial (NEXT-C) project, funded by NASA''s
Plume Impingement Studies in Space Environments for NASA …
Measure of Rarefication of a Flow: Kn < 0.01: Continuum Flow 0.01 < Kn < 0.1: Slip Flow 0.1 < Kn < 10: Transitional Flow Kn > 10: Free-Molecular Flow Transition from Continuum to Molecular Flow: Common to use the Bird Criteria (Bird, 1970) Computed
Multi-plume flow simulation of small bipropellant thrusters using parallel DSMC method …
As thruster #1′s position was right above the center of the solar panel, a huge amount of the plume gas particles from thruster #1 impacted on the upper surface of the solar panel. Thus, the maximum number flux and the heat flux were occurred at the center area of the upper surface of the solar panel.