Last edited by Shaktirr
Monday, May 11, 2020 | History

2 edition of High performance storable propellant resistojet found in the catalog.

High performance storable propellant resistojet

High performance storable propellant resistojet

final report.

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  • 7 Currently reading

Published by NASA Lewis Research Center, National Technical Information Service, distributor in Cleveland, OH, [Springfield, Va .
Written in English

    Subjects:
  • Electric propulsion.,
  • Performance tests.,
  • Resistojet engines.,
  • Rocket engine design.,
  • Spacecraft propulsion.,
  • Static firing.,
  • Stationkeeping.

  • Edition Notes

    SeriesNASA contractor report -- NASA CR-191128.
    ContributionsLewis Research Center.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL15409979M

    Mass Estimating Relations ENAE - Launch and Entry Vehicle Design U N I V E R S I T Y O F MARYLAND Propellant Tank Regression Data 5 y = x R2 = y = x R2 = 0 0 Tank Volume (m^3) Tank Mass (kg) LH2 Tanks LOX Tanks RP-1 Tanks. Propulsion for the Space Station requires a unique, challenging combination of features. The propulsion design must provide high performance to minimize propellant requirements, have extremely high reliability, provide an extended long-life capability, control emissions and outgasses that could impact in-space operations, and provide Cited by: 3.

    Hydrogen Helium Nitrogen Nitrous Oxide - Water -Ammonia TAI t Hydrazine 0 Consumed Heat, kJ/kg Figure 2 Theoretical performance comparison of resistojet propellants: specific impulse vs. heat required for heating propellant to the process temperature. 51st lAF Congress N o a 80 N t - 60 40 Cited by: In-Space Manufacture of Storable Propellants.

    On-Board Chemical Propulsion Technology [Brian D. Reed, Nasa Technical Reports Server (Ntrs)] on *FREE* shipping on qualifying offers. On-board propulsion functions include orbit insertion, orbit maintenance, constellation maintenance, precision positioningCited by: 6. An experimental program was conducted to characterize the circular coaxial injector concept for application with the space-storable gas/liquid propellant.


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High performance storable propellant resistojet Download PDF EPUB FB2

COVID Resources. Reliable information about the coronavirus (COVID) is available from the World Health Organization (current situation, international travel).Numerous and frequently-updated resource results are available from this ’s WebJunction has pulled together information and resources to assist library staff as they consider how to handle coronavirus.

Building on this base NASA embarked upon the High Performance Storable Propellant Resistojet (HPSPR) program to significantly advance the resistojet state-of-the-art. Higher performance thrusters promised to increase the market demand for resistojets and enable space missions requiring higher : C.

Vaughan. High Performance Resi stojets To advance storable propellant resistojets beyond the current state-of- the-art sec mission average specific impulse (ref. several efforts have been undertaken. Improved heat exchanger performance, longer-life higher- temperature heaters (ref. 21), and improved nozzle performance (refs.

22 and. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Cited by: 8. propellant technology is accommodated by reducing mission objectives and/or increasing enroute travel times sacrificing the science value per unit cost of the program.

Therefore, a high performance, storable, thruster utilizing fluorinated oxidizers with hydrazine is File Size: 1MB. The preliminary design of the storable variant (MON-3/MMH) has been performed by DLR. The Aestus II engine with a large nozzle expansion has been ratio chosen as baseline. A first iteration has demonstrated, that it indeed provides the best performance for the storable propellant combination, when considering all engines.

EXPERIMENTAL ROCKET PERFORMANCE OF APOLLO STORABLE PROPELLANTS IN ENGINES WITH LARGE AREA RATIO NOZZLES by Carl A. Aukerman and Arthur M. Trout Lewis Research Center SUMMARY The performance of nitrogen tetroxide and a blend of 50 percent hydrazine and 50 percent unsymmetrical dimethyl hydrazine (UDMH) was evaluated at a chamber pres-Cited by: 4.

The Space Storable Rocket Technology Program (SSRT) was conducted for NASA-LeRCby TRWto establish a technology base for a new class of high performance and long-life bipropellant engines using space storable propellants.

The results of the initial phase of this systematic multi-year program are described. Task 1 evaluated several. Full text of "NASA Technical Reports Server (NTRS) Material Compatibility with Space Storable Guidebook" See other formats. storable fuels such as hydrazine typically use nitrogen tetra oxide (N2O4) oxidizer, creating a propellant combination that is both storable and hypergolic.

Historical Perspectives All of the early rocket pioneers – Tsiolkovsky, Goddard and Oberth - concluded that, to achieve their performance aims, liquid propellant engines would be. American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA The 'Propellant Profiles' series does make good BACKGROUND REFERENCE for propellants, however, to safely perform ANY ammunition reloading from the content of these books would be impractical and foolish.

It is safe to say that propellant formulations are always subject to change, therefore, always refer to the latest, modern reloading manuals /5(34).

A first iteration has demonstrated, that it indeed provides the best performance for the storable propellant combination, when considering all engines available today or which may be available in a short- to medium term. The RD K engine has been proposed as alternative to reduce the development duration of the high-thrust by: 1.

The Free Molecule Micro-Resistojet (FMMR), a low cost, low power, high propellant storage density, and green propulsion system, has been analyzed in this study to determine its ability to provide.

Propulsion for the Space Station requires a unique, challenging combination of features. The propulsion requirements demand responsive capabilities for orbit control and countering on-board or externally induced forces, and precision control for station-keeping with minimum disturbances.

The propulsion design must provide high performance to minimize propellant requirements, have extremely Cited by: 3. The high performance resistojet also has relevance to existing small spacecraft busses. The information gathering exercise determined that for LEO spacecraft primes favoured a target ISP of greater than 80 s for a xenon resistojet with a power requirement of less than 50 W, target thrust level of 20–50 mN and total impulse of 10 by: 1.

Introduction. The current state of the art xenon resistojet has shown specific impulse, I sp, with xenon propellant up to 48 s utilised for small spacecraft below kg [, ].Such performance can result in either propellant mass savings or increased capability with respect to cold gas thrusters [].The primary application for a high performance resistojet is for primary propulsion on Cited by: 1.

From until resistojets were used for a limited number of space missions. Capability increased in stages from an initial application using a 90 W gN2.

The high deltaV and requirement for a gaseous propellant, as well as a propulsion wet mass upper limit of 20 kg including margins stretches the performance of the low power resistojet to the limit. Further missions, requiring high resolution imaging, such as 1 m resolution TOPSAT may require a reduction in orbit altitude from to as low as Cited by:   American Institute of Aeronautics and Astronautics Sunrise Valley Drive, Suite Reston, VA Cited by:.

Initial simulations suggest that the resistojet can attain a specific impulse of nearly 68 seconds with a thrust level of mN for a water vapor propellant, 40 expansion slots and a heated wall.AQUARIUS uses a storable, safe and non-toxic propellant: water, which allows for the design of all propulsion system below kPa, reduction of dry mass ratio and simplification of feed line.Air/LH2 Air/LH2 propellant.

The propellants tested and proposed for use in environmentally-friendly or high-speed jet engines. Ambient air (78 % nitrogen, 21% oxygen, etc.) is scooped up by air intakes and used in turbojet, turbofan, ramjet, scramjet, or other airbreathing engines as an oxidizer.