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3 edition of On-board propulsion system analysis of high density propellants found in the catalog.

On-board propulsion system analysis of high density propellants

Steven J. Schneider

On-board propulsion system analysis of high density propellants

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  • 13 Currently reading

Published by National Aeronautics and Space Administration, Lewis Research Center, National Technical Information Service, distributor in [Cleveland, Ohio], [Springfield, Va .
Written in English

  • Storable propellants,
  • Near Earth Asteroid Rendezvous Mission,
  • Liquid oxygen,
  • Hydroxyl compounds,
  • Hydrocarbon fuels,
  • Hydrazines,
  • Gun propellants,
  • Asteroid missions,
  • Attitude control,
  • Difluorides

  • Edition Notes

    Other titlesOn board propulsion system analysis of high density propellants.
    StatementSteven J. Schneider.
    SeriesNASA/TM -- 1998-208811., NASA technical memorandum -- 208811.
    ContributionsLewis Research Center.
    The Physical Object
    Pagination1 v.
    ID Numbers
    Open LibraryOL15544505M

      The propulsion system should be capable of stable throttling to (20% power). Space survival time of greater than 3 years. Ascent pump-fed engine development w lbf thrust and a minimum vacuum specific impulse of sec. The propulsion system should be capable of stable throttling to (20% power). Although it is now within mankind’s technical prowess to chin this high voltage bar, an electrical field of such magnitude is not implied by the numerous UFO sightings nor, more importantly, by the analysis of comparatively low voltage ionization radiation effects presented in Paul R. Hill’s more than helpful book, Unconventional Flying. The ground infrastructure and operations, which are largely driven by the type of propulsion system and propellants, was also included in the scope of support. No. 75 # of active on-board space sys. req’d for propulsion (-) %. High density hydrogen   Analysis of Self-Field MPD Thrusters for Designing a Megawatt-Class In-Space Propulsion System View Section, Azidonation Derivatives of 1,1',4,4'-TetramethylTetrazene as Nitrogen-Rich Compounds for NTO/MMH Replacement - Synthesis, Characterization and Properties.

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On-board propulsion system analysis of high density propellants by Steven J. Schneider Download PDF EPUB FB2

On-Board Propulsion System Analysis of High Density Propellants Steven J. Schneider* National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio Abstract The impact of the performance and density of on-board propellants on science payload mass of Discovery Program class missions is evaluated.

On-Board Propulsion System Analysis Of High Density Propellants (OCoLC) Microfiche version: Schneider, Steven J. On-board propulsion system analysis of high density propellants (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document Type: Internet Resource, Computer File.

On-Board Propulsion System Analysis Of High Density Propellants (OCoLC) Online version: Schneider, Steven J. (Steven Joseph). On-board propulsion system analysis of high density propellants (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors.

On-Board Chemical Propulsion NASA Lewis Research Center's On-Board Propulsion program (OBP) is developing low-thrust chemical propulsion technologies for both satellite and vehicle reaction control applications.

There is a vigorous international competition to. 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. High Energy Density Propellants.

New technologies in atom formulation and physics of material manipulation has led to the discovery and synthesis of materials that can be used in rocket propellants (Ref. 3, and see the attached extensive bibliography on high energy density materials).

Air-Breathing Launch Propulsion Systems TA Ancillary Propulsion Systems TA ACES Integrated Flight System 2. High Energy Density Propellants 3. SRM Composite Case Damage Tolerance and Technologies facilitating air-breathing launch propulsion system development High-Fidelity Integrated Propulsion Design Software.

– Integrated system design In-Space Propulsion Systems (JSC) has led the development and certification of a majority of NASA in-space on-board human spacecraft propulsion systems and is actively engaged in the development and demonstration of advanced propulsion system technologies.

The ft high vacuum ( torr) test chamber provides. The current work focuses on sizing and establishing critical design parameters On-board propulsion system analysis of high density propellants book dual chemical-electric propulsion systems that shall enable a stand-alone 16U CubeSat mission on a hybrid high.

S.1 Spacecraft Propulsion Systems Spacecraft propulsion is based on jet propulsion as used by rocket motors. The principle of rocket propulsion was known as far back as B.C. In the 13th century solid rocket-powered arrows were used by the Chinese military.

The Second World War and the cold war advanced rocket missile development in modern time. Spacecraft propulsion 3. below), rediscovered in by. Oberth. First practitioners who developed rocket technology were. R.H. Goddard inW. von Braunin (he developed the first reliable rocket, the V-2, the first device toFile Size: 1MB.

One of the most important selection criteria for the radiological part of a dirty bomb is the activity–mass relationship (specific activity, expressed in Bq g −1).Uranium, either naturally occurring or enriched to weapons grade (90% or greater U), has a low specific activity.

For U, the specific activity value is ×10 −5 Bq g −1.A mass of 25 kg of 90% U is a sufficient. A second approach would be to use a moderate-thrust ( lb), modest-performance chemical propulsion thruster at sec I sp, such as liquid oxygen (LOx)/monopropellant hydrazine using a cryocooler to keep the LOx from boiling ty changes of hundreds of feet per second can be achieved in minutes to hours, depending on the propellant mass available, for platforms of thousands.

The paper presents the development of the power, propulsion, and thermal systems for a 3U CubeSat orbiting Earth at a radius of km measuring the radiation imbalance using the RAVAN (Radiometer Assessment using Vertically Aligned NanoTubes) payload developed by NASA (National Aeronautics and Space Administration).

The propulsion system was selected as a Mars-Space PPTCUP -Pulsed Cited by: 2. The Bussard ramjet is a theoretical method of spacecraft propulsion proposed in by the physicist Robert W.

Bussard, popularized by Poul Anderson's novel Tau Zero, Larry Niven in his Known Space series of books, Vernor Vinge in his Zones of Thought series, and referred to by Carl Sagan in the television series and book Cosmos. Bussard proposed a ramjet variant of a fusion rocket capable. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA As stated in NextBigFuture, a US scientist, Guido Fetta, has built his own propellant-less microwave thruster, and managed to persuade NASA to test it out.

The test results were presented on July 30 at the 50th Joint Propulsion Conference in Cleveland, Ohio.

Astonishingly enough, they are positive. The dipole drive is a new propulsion system which uses ambient space plasma as propellant, thereby avoiding the need to carry any of its own.

The dipole drive remedies two shortcomings of the classic electric sail in that it can generate thrust within planetary magnetospheres and it can generate thrust in any direction in interplanetary space.

Calculate the propellant mass required to launch a kg spacecraft from a km-altitude circular earth orbit on a Hohmann transfer trajectory to the orbit of Saturn.

Calculate the time required for the mission and compare it with that of Cassini. Assume the propulsion system has a specific impulse of s. {Ans.: yr; 21, kg}. Project Apollo: A Feasibility Study of an Advanced Manned Spacecraft and System, Final Report – Volume IV On-Board Propulsion – Book 2, Appendix P-A.

General Electric (15 May ) ( MB Excerpt) Aerojet 2KS, Escape SRM. Thrust (sl): 23, lbf at ISP Chamber Pressure: 1, psia Burning Time: 2 seconds Propellant Mass: lbs.

A German V-2 became the first spacecraft when it reached an altitude of km in June in Peenemünde, Germany. Sputnik 1 was the first artificial was launched into an elliptical low Earth orbit (LEO) by the Soviet Union on 4 October The launch ushered in new political, military, technological, and scientific developments; while the Sputnik launch was a single event, it.

A new propulsion system being developed in Spain is both those things, and could help solve a growing problem with Earth’s satellites: the proliferation of space junk. An advanced concept of launch system from ground to orbit, called laser launch system, has been discussed.

As a kW-class fiber laser has been developed today, the laser propulsion is now a realistic option for launching microsatellites frequently at very low cost. In this chapter, we shall discuss several unresolved technical problems such as propulsion design and laser beam transmission Author: Koichi Mori.

Full text of "Propellant Management in Booster and Upper Stage Propulsion Systems" See other formats / — NASA-TM / - -5 - v ' 7 06/25/97 AN NA5A-in-i^«-» A/ - A PROPELLANT MANAGEMENT IN BOOSTER AND UPPER STAGE PROPULSION SYSTEMS Mark F.

Fisher National Aeronautics and Space Administration George C. Marshall Space Flight Center Huntsville, Alabama, USA Abstract A.

Washington, DC: The National Academies Press. doi: / The VAATE focus on (1) optimization of the propulsion system at the level of the air vehicle system, (2) an “affordable capability” goal, including both performance and cost metrics, and (3) planned synergy and dual-use with civil aeronautics requirements goes beyond the.

Along with overall mass limitations for a 1U and 3U CubeSat at kg and 4 kg, respectively, the maximum pressure contained in any component is limited to atmospheres. Due to the high energy density, low vapor pressure, and nontoxic characteristics of hydrogen peroxide, it is a promising choice for use in a CubeSat propulsion by: 3.

on board the rockets, and extremely high energies are achievable when the exhaust is accelerated by Of the liquid propellants used, density is worst for disjunctive drive, differential sail, and a hyperspace drive based upon the Heim sion system to power spaceships for Inter planetary travel may become a reality in near future.

@article{osti_, title = {Optimum performance of MHD-augumented chemical rocket thrusters for space propulsion applications}, author = {Schulz, R J and Chapman, J N}, abstractNote = {The use of magnetohydrodynamic (MHD) acceleration of a chemical rocket exhaust stream, to augment the thrust of small, space-propulsion type chemical thrusters was examined, with the purpose of identifying.

Propellants for these auxiliary thrusters have to be included in the propellant budget when they are supplied from the same feed system and tanks as the larger rocket engine.

Depending on the mission, the duty cycle, and the propulsion system concept, auxiliary propulsion systems may consume a significant portion of the budgeted propellants. Scope Title Reactor and Fuel System. Scope Description. The focus is on highly stable materials for nuclear fuels and non-fuel reactor components (i.e., moderator tie tubes, etc.) that can heat hydrogen to temperatures greater than K without undergoing significant dimensional deformation, cracking, or hydrogen reactions.

Solid Rocket • A solid rocket motor is a system that uses solid propellants to produce thrust • Advantages – High thrust – Simple – Storability – High density Isp • Disadvantages – Low Isp (compared to liquids) – Complex throttling – Difficult to stop and restart – Safety Mass Fractions Inert-mass fraction: SPAD, Eq minert = mass of propulsion system, excluding propellant and payload (i.e.

dry mass of only the propulsion system) Typical values: f inert = – for liquid-fueled rocket motors ( average) f inert = – for solid-fueled rocket motors ( average) f inert = –   This paper is dedicated to on-board terminal control systems.

Specific features of this class of systems are identified and an approach to terminal feedback control synthesis is proposed, being adequate to the nature of terminal problems. Theoretical and practical problems in on-board terminal systems design for liquid-propellant carrier rockets are : A.

Andrienko, V. Ivanov. Micro-propulsion based on vacuum arcs Journal of Applied Physics( Electric propulsion systems have very high specific impulses in the range of thousands of seco57 J. These satellites have limited space on board and carrying a propulsion system for the EOL deorbiting burn is often not by: 1.

This book, a translation of the French title Technologie des Propergols Solides, offers otherwise unavailable information on the subject of solid propellants and their use in rocket fundamentals of rocket propulsion are developed in chapter one and detailed descriptions of concepts are covered in the following chapters.

It’s also an interesting potential propulsion system for use anywhere in the Inner Solar System where the energy of the Earth-orbit SPS system can be used.

Kantrowitz proposed the concept of the laser-energized rocket in the late s when the potential of the high-powered lasers being developed for possible military uses was under. NASA Images Solar System Collection Ames Research Center. Brooklyn Museum. Full text of "DTIC ADA Isomer Energy Source for Space Propulsion Systems".

aft propulsion system (subsystem) APS: ascent propulsion system: APS: attitude propulsion system (subsystem) APS: automated planning system: APS: automatic processing system: APS: auxiliary power subsystem: APS: auxiliary propulsion system: APSAP: auxiliary propulsion system aft pod: APSE: Ada programming support environment: APSS: atmospheric.

Hello, and welcome to Beyond NERVA. Here, we look at the technology that will enable humanity to expand into the solar system, and eventually the stars. It’s a trope in the space industry to comment after each failure that “space is hard.” The difficulties facing even now-routine space missions are.

The thrusters feature non-reactive ionic salt propellants and a design without moving parts or pressurization, relying on capillary forces alone.

Each propulsion system weighs about grams and fits in a 9 x x cm envelope (about U), including propellant and power and control electronics.

Disclosed herein are two separate processes that do not require a propellant and do not produce an equal and opposite reaction against any external form of matter in the Local Inertial Reference Frame and do not violate Newton's Laws in the Universal Reference Frame. The first process produces horizontal motion, relies on the earth's gravitational field as an external force, and has been Cited by: A dipolar force field propulsion system having a alternating electric field source for producing electromotive lines of force which extend in a first direction and which vary at a selected frequency and having an electric field strength of a predetermined magnitude, a source of an alternating magnetic field having magnetic lines of force which extend in a second direction which is at a Cited by: Service Propulsion Propellants The service propulsion system was used on for the first midcourse correction.

The propellant loadings listed in the following table were calculated from gaging system readings and measured densities prior to lif't-off. Loaded In tanks In lines Total Consumed Remaining at tim e of incident Fuel, lb 15