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4 edition of Effect of voltage level on power system design for solar electric propulsion missions found in the catalog.

Effect of voltage level on power system design for solar electric propulsion missions

Effect of voltage level on power system design for solar electric propulsion missions

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Published by National Aeronautics and Space Administration, Glenn Research Center, Available from NASA Center for Aerospace Information, National Technical Information Center [distributor in [Cleveland, Ohio], Hanover, MD, Springfield, VA .
Written in English


Edition Notes

StatementThomas W. Kerslake.
SeriesNASA/TM -- 2003-212304., NASA technical memorandum -- 212304.
ContributionsNASA Glenn Research Center.
The Physical Object
FormatMicroform
Pagination1 v.
ID Numbers
Open LibraryOL17635034M
OCLC/WorldCa56799261

In this tutorial, we will use GMAT to perform a finite burn for a spacecraft using an electric propulsion system. Note that targeting and design using electric propulsion is identical to chemical propulsion and we refer you to the tutorial named Target Finite Burn to Raise Apogee for targeting configuration. This tutorial focuses only on configuration and modelling using electric propulsion. On Tuesday, Ap , NASA awarded a contract to Aerojet Rocketdyne, Inc. to design and develop an advanced electric propulsion system that will significantly advance the nation’s commercial space capabilities, and enable deep space exploration missions, including the robotic portion of NASA’s Asteroid Redirect Mission (ARM) and its journey to Mars.

  NASA has selected Aerojet Rocketdyne, Inc. of Redmond, Washington, to design and develop an advanced electric propulsion system that will significantly advance the nation's commercial space capabilities, and enable deep space exploration missions, including the robotic portion of NASA's Asteroid Redirect Mission (ARM) and its Journey to Mars. Design and Construction of a Solar Hybrid Car (Electric Motor and Human Propulsion) 45 Determination of the Required Power Power demand (9 6) in a moving vehicle is defined by the product of overall strength and reached speed. The total force FT is defined by the sum of all the resistive forces []: Force due to the slope Fθ, tire.

Planetary mission performance is presented for small, low power Solar Electric Propulsion spacecraft launched on a Delta II () launch vehicle. The planetary missions presented in this paper are those that appear most attractive for a small, lowcost solar electric propulsion by:   Under the current mission guidelines, the robotic probe would launch in and bring the rock to the Earth-moon system in , with humans launching to it by or earlier.


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Effect of voltage level on power system design for solar electric propulsion missions Download PDF EPUB FB2

EFFECT OF VOLTAGE LEVEL ON POWER SYSTEM DESIGN FOR SOLAR ELECTRIC PROPULSION MISSIONS Thomas W. Kerslake National Aeronautics and Space Administration Glenn Research Center Cleveland, Ohio Phone: Fax: Email: [email protected] ABSTRACT This paper presents study results quantifying the.

Effect of Voltage Level on Power System Design for Solar Electric Propulsion Missions Article in Journal of Solar Energy Engineering (3) May with 31 Reads How we measure 'reads'. This paper presents study results quantifying the benefits of higher voltage, electric power system designs for a typical solar electric propulsion spacecraft Earth orbiting mission.

A conceptual power system architecture was defined and design points were generated for several system voltages using state-of-the-art or advanced by: 2. This paper presents study results quantifying the benefits of higher voltage, electric power system designs for a typical solar electric propulsion spacecraft Earth orbiting mission.

A conceptual power system architecture was defined and design points were generated for system voltages of V, V, V and V using state-of-the-art or Cited by: 9. the power source for solar-electric propulsion (SEP) missions [].

The current plan for the In this propulsion system, high-power photovoltaic arrays provide energy's to a xenon-fueled electrical engine. One of the proposed applications of the high-power SEP technology is File Size: 5MB.

Solar electric propulsion (SEP) refers to the combination of solar cells and electric thrusters to propel a spacecraft through outer space. This technology has been exploited in a variety of spacecraft by the European Space Agency, the Japanese Space Agency, Indian Space Research Organisation and NASA.

SEP has a significantly higher specific impulse than normal chemical rockets, thus requiring. Get this from a library.

Effect of voltage level on power system design for solar electric propulsion missions. [Thomas W Kerslake; NASA Glenn Research Center.]. missions, the onboard propulsion systems and their required propellant may make up more than half of the overall spacecraft mass.

By utilizing solar electric propulsion (SEP), the mass of the propulsion system and propellant can be reduced by up to 90 percent by.

Frequently Asked Questions. History of NASA's involvement. Hear DS1's radio signals. SOLAR ELECTRIC (ION) PROPULSION. Click here to see a time lapse video ( MB Quicktime movie) of the DS1 Ion Thruster Compatibility Test taped on Febru (Or you can get a smaller version: MB).This testing was carried out on the DS1 spacecraft in the Solar Thermal Vacuum Chamber at JPL.

Solar Electric Propulsion (SEP) trajectories are shown for Mars missions between late and 1. Mission performance is presented as burn-out mass along contours of constant flight time. The Solar Electric Propulsion project is developing large solar arrays and high-power electric thrusters for an integrated in-space test-flight.

Compared with current conventional chemical propulsion systems, at launch it will weigh two times less and use four times less storage for the electricity produced, and will operate at radiation levels. Electric Propulsion Options and Trades • Benefits: • Much higher specific impulse • Arcjets – s • Hall Thrusters – – s • Ion thrusters – – 10,s • Other concepts (VASIMIR, MPD, PIT) in same range • Higher Isp results in much lower propellant mass • Trades: • Need external source of power and electronics to match to the thruster.

spacecraft propulsion. With literally hundreds of electric thrusters now operating in orbit on communications satellites, and ion and Hall thrusters both having been successfully used for primary propulsion in deep-space scientific missions, the future for electric propulsion has arrived.

An electrically-powered spacecraft propulsion system uses electrical, and possibly also magnetic fields, to change the velocity of a of these kinds of spacecraft propulsion systems work by electrically expelling propellant (reaction mass) at high speed. Electric thrusters typically use much less propellant than chemical rockets because they have a higher exhaust speed (operate.

• Solar electric propulsion allows deep-space missions to carry more cargo and use smaller launch vehicles while reducing mission costs. • The Solar Electric Propulsion project has developed solar arrays that are lighter, stronger, more compact, and less expensive than those currently available.

The solar electric propulsion system of the European Space Agency's SMART-1 spacecraft used a Snecma PPSG Hall thruster. the author mentions another potential use for the technology behind Space Solar Power could be for Solar Electric Propulsion Systems that could be used for interplanetary human exploration missions.

enabled by Solar Electric Propulsion and Advanced Modular Power systems. Most, if not all of these concepts can be made to fit within a $ million Discovery Mission cost cap. In addition, we have proposed further reducing spacecraft cost by using a common bus for deep space missions. With the recently announced, commercially.

• The Solar Electric Propulsion project has developed solar arrays that are lighter, stronger, more compact, and less expensive than those currently available. • Solar electric propulsion provides such high fuel economy that it reduces the amount of propellant required onboard vehicles for deep-space missions by as much as 90 percent.

Introduction. The feasibility and performance study of Solar Electric Propulsion (SEP) systems for space exploration is the subject of a number of recent investigations.In particular, the scientific implications have much increased with the recognition that new advances in SEP technology have significantly reduced the costs and risks of using ion thruster as a primary Cited by:   Advanced solar electric propulsion will be needed for future human expeditions into deep space, including to Mars.

Shown here is a kilowatt Hall thruster being evaluated at NASA's Glenn Author: Dc Agle. The power level along with the design specific impulse (ISP) and specific mass for a SEP system play a significant role in determining how effective the propulsion system may be for delivering cargo during each mission opportunity for the Mars architecture.

3. The space agency has awarded California-based company Aerojet Rocketdyne a $67 million, month contract to design, build and test an advanced, superefficient solar .Advanced Solar & Nuclear Electric Propulsion Systems for Asteroid Deflection 7 ADVANCED CONCEPTS TEAM Mission Drivers sesah pno i ss•Mi Earth spiral out NEA rendez-vous NEA spin axis change NEA push NEA coast Earth Launch miss Total response time Inject Orbit, T/M s/c, Isp NEA orbit, T/M s/c, Isp NEA spin state, mass, size, T s/c Rem-aining File Size: KB.