4 edition of Multi-axis thrust measurements of the EO-1 pulsed plasma thruster found in the catalog.
Multi-axis thrust measurements of the EO-1 pulsed plasma thruster
by National Aeronautics and Space Administration, Glenn Research Center, National Technical Information Service, distributor in [Cleveland, Ohio], [Springfield, Va
Written in English
|Statement||Lynn A. Arrington, Thomas W. Haag.|
|Series||NASA/TM -- 1999-209396., NASA technical memorandum -- 209396.|
|Contributions||Haag, Thomas W., NASA Glenn Research Center.|
|The Physical Object|
Thrust Measurement Areas of Development: In-Frame Calibration System Multi-Axis Thrust Frame includes a complete force measuring module along with Publication» Multi-Axis Thrust Measurements of the EO-1 Pulsed Plasma Thruster. Pulsed Plasma Thruster Propulsion System Final Presentation May 4, • Plasma acceleration generates thrust. Thruster Design Current Flow Teflon Anode - Cathode + High Voltage Source Teflon Pulse Plasma Thruster Basic Stamp Relay. System .
Title: Multiple Plasma Stream Electromechanical Model for Pulsed Plasma Thruster. Authors: Kaartikey Misra (Submitted on 23 Apr ) Abstract: Conventional snowplow/1-D models assume the existence of single completely ionized plasma sheet in the discharge chamber of pulsed plasma thrusters (PPTs). However, extensive experimental analysis and Author: Kaartikey Misra. Performance of a kW class applied field MPD thruster [electronic resource] / Maris A. Mantenieks, . Evaluation of low power hall thruster propulsion [microform] / David Manzella [et al.] Multi-axis thrust measurements of the EO-1 pulsed plasma thruster [microform] / Lynn A. Arrington, Thoma.
A model of the near field plasma plume of a Pulsed Plasma Thruster (PPT) is developed. As a working example we consider a micro-PPT developed at the Air Force Research Laboratory. This is a miniaturized design of the axisymmetric PPT with a thrust in the 10 N range that utilizes Teflon TM as a . Abstract: The ElectroMagnetic Plasmoid Thruster (EMPT) at MSNW LLC. is a 1 kW, electrodeless pulsed plasma thruster that generates and accelerates a Field Reversed Configuration (FRC) to produce thrust. Two key components of the thruster are .
Bronchopulmonary diseases and related disorders
story of the Waldorf-Astoria
Observation, record keeping and classroom management
The Miracle of Pi-Water
Northern Photographic Exhibition
art of scientific investigation.
On the solvability of equations in incomplete finite fields.
National pensions policy initiative
Metaphysics in Islamic Philosophy (Studies in Islamic philosophy and science)
100 years, 100 artefacts
British Columbia Personal Property Security Act handbook
Larson Precalculus With Limits Hybrid CD Advanced Placement
The book of modern composers.
MULTI-AXIS THRUST MEASUREMENTS OF THE EO-1 PULSED PLASMA THRUSTER Lynn A. Arrington Dynacs Engineering Company, Inc. NASA John H. Glenn Research Center Cleveland, OH Thomas W. Haag NASA John H. Glenn Research Center Cleveland, OH Abstract Pulsed plasma thrusters are low thrust propulsive devices which have a high specific impulse at low power.
Multi-axis thrust measurements of the EO-1 pulsed plasma thruster (OCoLC) Material Type: Document, Government publication, National government publication, Internet resource: Document Type: Internet Resource, Computer File: All Authors / Contributors: Lynn A Arrington; Thomas W Haag; NASA Glenn Research Center.
Multi-axis thrust measurements of the EO-1 pulsed plasma thruster (OCoLC) Material Type: Government publication, National government publication: Document Type: Book: All Authors / Contributors: Lynn A Arrington; Thomas W Haag; NASA Glenn Research Center.
Pulsed plasma thrusters are low thrust propulsive devices which have a high specific impulse at low power. A pulsed plasma thruster is currently scheduled to fly as an experiment on NASA's Earth Observing-1 satellite mission.
The pulsed plasma thruster will be used to replace one of the reaction : Thomas W. Haag and Lynn A. Arrington. Pulsed Plasma Thruster for Multi-Axis CubeSat Attitude Control Applications. Aditya R. Khuller, Omar Alavi, Joseph Mayer, Tyler J. Lanes, Patrick Needham, Surya S. Rajagopalan, Ashley Curiel, Dominic Bonelli, Erskine Thompson, Ryley Miller, Madison Grayson, Noah Sandys, Daniel B.
Image left: EO - 1 Earth orbiter flight pulsed plasma thruster. Credit: NASA The Earth Observing 1 (EO - 1) spacecraft, launched inuses one dual-axis PPT for pitch axis control and momentum management.
The EO - 1 PPT was developed at the NASA Glenn Research Center and produced by Primex Aerospace Company. Figure 2 The EO-1 Pulsed Plasma Thruster System InNASA Lewis Research Center initiated a program with Primex Aerospace Co.
to develop, fabricate, and flight qualify a PPT that improved significantly on the then current state of the art. The result of that program is the Earth Observer-1 (EO-1) PPT, which is scheduled to. The specific impulse of the 13 cold gas micronewton thrusters flight models has been measured for thrust levels in the range of – μ N, showing a slight increase of I sp from around 50 to 63 s with thrust for all flight by: 7.
From a structural point of view ADD SIMP-LEX is a parallel plate ablative pulsed plasma thruster based on two copper electrodes separated by a 10 μ m Kapton ® by: A pulsed magnetoplasmadynamic thruster uses energy stored in a capacitor bank to create and to ionize plasma from a block of solid propellant in a very high current discharge pulse.
After charging the capacitors, controlled thruster ignition is realized using a spark by: 9. A torsional-type thrust stand has been designed and built to test pulsed plasma thrusters in both single shot and repetitive operating modes.
Using this stand, momentum per pulse is determined strictly as a function of thrust stand deflection, spring stiffness, and natural frequency. No empirical corrections are required. The accuracy of the method was verified using a swinging impact by: A pulsed plasma thruster (PPT), also known as a plasma jet engine, is a form of electric spacecraft propulsion.
PPTs are generally considered the simplest form of electric spacecraft propulsion and were the first form of electric propulsion to be flown in space, having flown on two Soviet probes (Zond 2 and Zond 3) starting in PPTs are generally flown on spacecraft with a surplus of. A Micro Pulsed Plasma Thruster (PPT) for the interdi sciplinary book t o be publi shed in by.
Multi-Axis Thrust Measurements of the EO-1 Pulsed Plasma Thruster. Article. design philosophy allows the balance to measure impulse bits (Ibit) in the range of 20– μNs typical of pulsed plasma thrusters (PPTs) for pico- and nano-satellites.
The uncertainty in the Ibit measurement is quantiﬁed to be about %, smaller than the typical values of this kind of balance (between 12% and 15%).
This has been possible. A b s t r a c t: Pulsed Plasma Thruster (PPT) is one of the promising electric propulsion devices for the small satellite as the following advantages: simplicity, lightweight, robustness, and low power consumptions.
Moreover PPT can generate a very small impulse bit with high specific impulse at optional time interval. Therefore PPT has great advantages as a precision atti tude control system. Abstract: A pulsed plasma thruster (PPT) is one of the electric propulsions for small satellites less than kg.
Though some kinds of thrust stands can measure impulse bits, there are few examples that mass shots of PPTs have been measured by thrust stands. In this. Study of Plasma Parameter Distributions in Low Power Hall Effect and Ablative Pulsed Plasma Thrusters Article March with 4 Reads How we measure 'reads'.
AIAA “Multi-Axis Thrust Measurements of the EO-1 Pulsed Plasma Thruster” – Determine thrust and impulse bit across throttle range – Before and after life testing - no change – Evaluate off-axis impulse bit component – Characterize shot-to-shot repeatability Charge Duration (msec) 0 These thruster clusters, pictured at right, feature the following • Precise, pulsed impulse bits (80μN-s) • Direct flight heritage • Solid propellant – no pressurized containers, no moving parts • Low power: multiplexed array of 9 μPPTs was constructed and delivered to the Air Force Institute of Technology as a lab- model test unit.
A Thrust Stand for Liquid Propellant Pulsed Plasma Thrusters Hiroyuki Koizumi*1, Akira Kakami, Kimiya Komurasaki*2, and Yoshihiro Arakawa*3 University of TokyoHongo, Bunkyo-ku, TokyoJAPAN (E-mail: [email protected]) Abstract A torsional-type thrust stand is designed, to precisely.
A. Pulsed plasma thruster and vacuum system The experimental PPT had an oil capacitor rated for a maximum voltage of 2 kV with a capacitance of 10 µF. This corresponds to a maximum discharge energy of 20 J.
The electrode length and spacing was 15 and 20 mm, respectively. A side view of a single pulse discharge is shown in Fig. 1. An example of the discharge voltage and current of a single. PPT Validation (2 of 5) Earth Observing-1 Mission Technology Forum Functionality – Benchtop and vacuum testing – Demonstrate range of planned orbital operations – Throttling through charge duration control ( - msec) Performance AIAA “Multi-Axis Thrust Measurements of the EO-1 Pulsed Plasma Thruster” Side 1 nominal at.General Dynamics Space Systems Division Redmond,WA Abstract.
The Pulsed Plasma Thruster (PPT) Experiment on the Earth Observing 1 (EO-1) spacecraft has demonstrated the capability of a new generation PPT to perform spacecraft attitude control.