A Highly Miniaturized μppt Thruster for Attitude Orbit Control
|
|
|
- Prosper Goodman
- 5 years ago
- Views:
Transcription
1 A Highly Miniaturized μppt Thruster for Attitude Orbit Control Junquan Li, Steve Greenland, Clyde Space Ltd, Glasgow UK, Mark Post, University of Strathclyde, Glasgow, UK Michele Coletti, Mars Space Ltd, Southampton, UK Contact
2 Presentation Outline PPTCUP Development and Nanosatellite PPTCUP Model PPTCUP Testing Results PPTCUP Orbit Keeping and Formation Control Simulation Results Conclusions
3 1. Pulsed Plasma Thruster and Nanosatellite Current PPT/Nanosatellite Future PPT/Nanosatllite
4 2. Pulsed Plasma Thruster Model a. Modified Nozzle Inductance of PPTCUP h: distance between electrode; l: length of electrodes; w: width of electrodes b. Motion of the Plasma Bulk T: total force; m: mass of the current sheet; F: pulse frequency;i: total current;u0 the magnetic permeability Lorentz Force Gas Dynamic Expansion Te: plasma electron temperature; R: molar gas constant; r Ratio of specific heats,r=1.3 for Teflon
5 2. Pulsed Plasma Thruster Model c. Circuit Equations of PPT V0: initial voltage; c: capacitance of capacitor; Rc.Re.Rpe.Rp: resistance of capacitor, wires and leads, plate electrodes and plasma; Lc.Le: inductance of capacitor, wires and leads; ne: electron density; \tau: characteristic pulse time; \xi: current sheet thickness F: pulse frequency;i: total current;u0 the magnetic permeability d. Impulse Bit of PPT Mn: mass of neutral gases mixture; Vdec: velocity of decomposed material
6 3.Pulsed Plasma Thruster Testing Results d. Impulse Bit of PPT Vibration Test and Vacuum Chamber used for Performances Test (Mars Space Ltd/IAC14-C.4.10)
7 Case 1: PPTCUP Orbit Keeping a. Life Time; b. Change in orbit semi major axis per revolution L:Life Time; Ah: Atmospheric scale height; a semi major axis Cd: drag coefficient; A:satellite cross sectional area; m:satellite mass c. Non-singular Equinoctial Orbit elements (NSEOE) instead of the classical orbital elecments (COE) Changes of semimajor axis Due to the aerodynamic drag Min
8 Case 1: PPTCUP Orbit Keeping Altitude Size Natural Life Life with PPT Increase Life 250km 1u 2u 3u 5.7d 11d 17d 17d 22d 28d 200% 100% 66% 350km 1u 2u 3u 2m 8d 4m 16d 6m 24d 5m 21d 8m 10m 8d 150% 75% 50% 450km 1u 2u 3u 1y 5m 2y 10m 4y 2m 3y 3m 4y 8m 6y 133% 67% 44%
9 Case 2 PPT Formation Flying/rendezvous/docking/In orbit Servicing Modelling: Hill Clohessy and Wiltshire Equations, considering Relative J_2 effects between the leader satellite and the follower satellite (or the mothership and the servicing satellite); U=Control, D=J_2. Follower/Servicing satellite Leader/Mothership
10 Case 2 PPT Formation Flying/rendezvous/docking/In orbit Servicing Satellite Orbit and PPT Parameters Mass of Satellite 4kg Formation Size 1km Circular Projected Formation Formation Initial Errors: 10m, 10 m, 10m Mass of PPT 180g mass+90g electrics Dimensions 90.17mmx95.89mmx31mm Total Impulse 42Ns Specific Impulse 608s Power 0.3-4w Thrust to Power ratio 20uN/w Impulse Bit 40uNs Altitude 350 km Electricity 0 degree Inclination 0 degree
11 PPT controller design: Asymptotic Second-order Sliding Mode Control l(2nd SMC) l l Sliding plane Proposed 2nd SMC Build Lyapunov functions Locally Asymptotically Stable
12 PPT controller design: Asymptotic Second-order Sliding Mode Control l(2nd SMC) l l l Sliding plane Proposed 2nd SMC PPT Modulator Output is calculated as:
13 Case 2 PPT Formation Flying/rendezvous/docking/In orbit Servicing Formation Shape/Size 1 km Formation Shape/Size 0.1 km
14 Case 2 PPT Formation Flying/rendezvous/docking/In orbit Servicing Formation Size 1 km Control Input Formation Size 0.1 km Control Input
15 Case 2 PPT Formation Flying/rendezvous/docking/In orbit Servicing Formation Size 1 km PPT Impulse Profile
16 Case 2 PPT Formation Flying/rendezvous/docking/In orbit Servicing Formation Size 0.1 km PPT Impulse Profile in 4 orbits
17 Case 2 PPT Formation Flying/rendezvous/docking/In orbit Servicing Formation Shape/Size 0.1 km Using XYZ Thruster Using X and Y thrusters only
18 Case 2 PPT Formation Flying/rendezvous/docking/In orbit Servicing Thruster/Time Formation Size 0.1 km PPT Impulse Profile X and Y Thruster Only
19 Case 2 PPT Formation Flying/rendezvous/docking/In orbit Servicing Formation Shape/Size 0.1 km Using X and Z Thrusters only Using X and Y thrusters only
20 Case 2 PPT Formation Flying/rendezvous/docking/In orbit Servicing Formation Size 0.1 km PPT Impulse Profile X and Z Thruster only
21 Conclusions 1. Miniaturization of PPTCUP and Nanosatellite by Clyde Space, Mars Space and the University of Southampton, final qualification testing. 2. PPTCUP can provide 40uN-80uN thrust pulse 1 million times in succession. 3. PPTCUP testing results and simulation results show that PPTCUP is capable for nanosatellite missions. 4. Future works: Numerical Optimization using mathematical model and new configurations of PPTCUP for precise attitude control.
22 Thank You for Listening!
Propulsion means for CubeSats
Propulsion means for CubeSats C. Scharlemann and D. Krejci 2009 CubeSat Developers Workshop, San Louis Obispo, CA Welcome to the Austrian Research Centers Space Propulsion & Advanced Concepts Staff: 11
PPT development for Nanosatellites applications: experimental results
PPT development for Nanosatellites applications: experimental results IEPC-213-198 Presented at the 33rd International Electric Propulsion Conference, The George Washington University Washington, D.C.
PROGRESS ON THE DEVELOPMENT OF A PULSED PLASMA THRUSTER FOR THE ASTER MISSION
PROGRESS ON THE DEVELOPMENT OF A PULSED PLASMA THRUSTER FOR THE ASTER MISSION IEPC-2013-318 Presented at the 33rd International Electric Propulsion Conference, The George Washington University Washington,
(b) Analyzed magnetic lines Figure 1. Steady state water-cooled MPD thruster.
A. MPD thruster In this study, as one of the In-Space Propulsion projects by JAXA (Japan Aerospace exploration Agency), a practical MPD propulsion system was investigated. We planned to develop MPD thrusters
Electric Rocket Engine System R&D
Electric Rocket Engine System R&D In PROITERES, a powered flight by an electric rocket engine is planed; that is, orbital transfer will be carried out with a pulsed plasma thruster (PPT). We introduce
Preliminary Development of an Experimental Lightweight Pulsed Plasma Thruster for Solar Sail Attitude Control
Preliminary Development of an Experimental Lightweight Pulsed Plasma Thruster for Solar Sail Attitude Control Kevin Pryor, Bong Wie, and Pavlos Mikellides Arizona State University 18 th Annual AIAA/USU
Plasma Behaviours and Magnetic Field Distributions of a Short-Pulse Laser-Assisted Pulsed Plasma Thruster
Plasma Behaviours and Magnetic Field Distributions of a Short-Pulse Laser-Assisted Pulsed Plasma Thruster IEPC-2015-91325 Presented at Joint Conference of 30th International Symposium on Space Technology
DESIGNED TO OUTPERFORM. Morpheus Space The Cradle of Innovation
DESIGNED TO OUTPERFORM Morpheus Space The Cradle of Innovation 2 Morpheus Space nanofeep HIGHEST EFFICIENCY Dynamic Thrust Range 1 µn - 40 µn Nominal Thrust 20 µn Specific Impulse 3000 to 8500 s Propellant
High Pulse Repetition Frequency Operation of Low-power short-pulse Plasma Thruster
High Pulse Repetition Frequency Operation of Low-power short-pulse Plasma Thruster IEPC-2015-91035 Presented at Joint Conference of 30th International Symposium on Space Technology and Science 34th International
IEPC Presented at the 35th International Electric Propulsion Conference Georgia Institute of Technology Atlanta, Georgia USA
Research and Development of Electrothermal Pulsed Plasma Thruster Systems for Powered Flight onboard the Osaka Institute of Technology 2nd PROITERES Nano-Satellite IEPC-2017-89 Presented at the 35th International
Influence of Electrode Configuration of a Liquid Propellant PPT on its Performance
Influence of Electrode Configuration of a Liquid Propellant PPT on its Performance IEPC-- /ISTS--b- Presented at Joint Conference of th International Symposium on Space Technology and Science th International
The Applicability of Pulsed Plasma Thrusters to Rendezvous and Docking of Cubesats
The Applicability of Pulsed Plasma Thrusters to Rendezvous and Docking of Cubesats IEPC-213-424 Presented at the 33 rd International Electric Propulsion Conference, The George Washington University, Washington,
Initial Experiments of a New Permanent Magnet Helicon Thruster
Initial Experiments of a New Permanent Magnet Helicon Thruster J. P. Sheehan 1, B. W. Longmier 1, I. M. Reese 2, T. A. Collard 1, F. H. Ebersohn 1, E. T. Dale 1, B. N. Wachs 1, and M. E. Ostermann 1 1
Analytical Modeling of a Microthruster System for Nanosatellite Applications
Master of Science Thesis Analytical Modeling of a Microthruster System for Nanosatellite Applications Veronica Wallängen Department of Theoretical Physics, School of Engineering Sciences Royal Institute
Performance Characteristics of Electrothermal Pulsed Plasma Thrusters with Insulator-Rod-Arranged Cavities and Teflon-Alternative Propellants
Performance Characteristics of Electrothermal Pulsed Plasma Thrusters with Insulator-Rod-Arranged Cavities and Teflon-Alternative Propellants IEPC-2007-337 Presented at the 30 th International Electric
Flight Demonstration of Electrostatic Thruster Under Micro-Gravity
Flight Demonstration of Electrostatic Thruster Under Micro-Gravity Shin SATORI*, Hiroyuki MAE**, Hiroyuki OKAMOTO**, Ted Mitsuteru SUGIKI**, Yoshinori AOKI # and Atsushi NAGATA # * Hokkaido Institute of
Pico-Satellite Orbit Control by Vacuum Arc Thrusters as Enabling Technology for Formations of Small Satellites
1/25 Pico-Satellite Orbit Control by Vacuum Arc Thrusters as Enabling Technology for Formations of Small Satellites Igal Kronhaus, Mathias Pietzka, Klaus Schilling, Jochen Schein Department of Computer
Asteroid Impact Mission AIM Workshop. Electric Propulsion for Attitude & Orbit Control
Asteroid Impact Mission AIM Workshop Electric Propulsion for Attitude & Orbit Control ESA, ESTEC, Noordwijk, The Netherlands, 22-23 February 2016 Christophe R. Koppel Consulting Ind., 75008 Paris, France
Miniature Vacuum Arc Thruster with Controlled Cathode Feeding
Miniature Vacuum Arc Thruster with Controlled Cathode Feeding Igal Kronhaus and Matteo Laterza Aerospace Plasma Laboratory, Faculty of Aerospace Engineering, Technion - Israel Institute of Technology,
Micro Pulsed Plasma Thruster Development
Micro Pulsed Plasma Thruster Development IEPC-7-15 Presented at the 3 th International Electric Propulsion Conference, Florence, Italy September 17-, 7 S. J. Pottinger * and C. A. Scharlemann Austrian
Development of Microwave Engine
Development of Microwave Engine IEPC-01-224 Shin SATORI*, Hiroyuki OKAMOTO**, Ted Mitsuteru SUGIKI**, Yoshinori AOKI #, Atsushi NAGATA #, Yasumasa ITO** and Takayoshi KIZAKI # * Hokkaido Institute of Technology
Low Cost Helicon Propulsion System for CubeSat future mission scenarios. T4i - University of Padova D.Pavarin
Low Cost Helicon Propulsion System for CubeSat future mission scenarios T4i - University of Padova D.Pavarin Centro di Ateneo Studi e Attività Spaziali University of Padova Padova, Italy Technology for
Helicon Plasma Thruster Persepective and At University of Padua
Helicon Plasma Thruster Persepective and Development status and future development At University of Padua D.Pavarin, M.Manente, F.Trezzolani, A.Selmo, M.Magarotto, E.Toson Outline Helicon Thruster overview
Two-stream Model of the Pulsed Plasma Thruster and Simulation Research
Two-stream Model of the Pulsed Plasma Thruster and Simulation Research IEPC-017-31 Presented at the 35th International Electric Propulsion Conference Georgia Institute of Technology Atlanta, Georgia USA
Research and Development on Coaxial Pulsed Plasma Thruster with Feed Mechanism
Research and Development on Coaxial Pulsed Plasma er with Feed Mechanism IEPC-2009-255 Presented at the 31st International Electric Propulsion Conference, University of Michigan, Ann Arbor, Michigan, USA
Evaluation of Pulsed Plasma Thruster System for µ-lab Sat II *
Evaluation of Pulsed Plasma Thruster System for µ-lab Sat II * Haruki TAKEGAHARA, Miwa IGARASHI, Naoki KUMAGAI, Kensuke SATO, and Kouji TAMURA Tokyo Metropolitan Institute of Technology, Dept. of Aerospace
Space Travel on a Shoestring: CubeSat Beyond LEO
Space Travel on a Shoestring: CubeSat Beyond LEO Massimiliano Vasile, Willem van der Weg, Marilena Di Carlo Department of Mechanical and Aerospace Engineering University of Strathclyde, Glasgow 5th Interplanetary
Research and Development of High-Power Electrothermal Pulsed Plasma Thruster Systems for Osaka Institute of Technology 2nd PROITERES Nano-Satellite
Research and Development of High-Power Electrothermal Pulsed Plasma Thruster Systems for Osaka Institute of Technology 2nd PROITERES Nano-Satellite IEPC-2015-22 /ISTS-2015-b-22 Presented at Joint Conference
Electric Propulsion Survey: outlook on present and near future technologies / perspectives. by Ing. Giovanni Matticari
Electric Propulsion Survey: outlook on present and near future technologies / perspectives by Ing. Giovanni Matticari Electric Propulsion: a concrete reality on many S/C GOCE ARTEMIS ARTEMIS SMART-1 EP
Physics Assessment Unit A2 2
Centre Number 71 Candidate Number ADVANCED General Certificate of Education 2014 Physics Assessment Unit A2 2 assessing Fields and their Applications AY221 [AY221] MONDAY 9 JUNE, MORNING TIME 1 hour 30
Micro Electric Propulsion Technology for Small Satellites: Design, Testing and In-Orbit Operations
SSC13-III-9 Micro Electric Propulsion Technology for Small Satellites: Design, Testing and In-Orbit Operations V.J. Lappas, T. Harle, A. Knoll, P. Shaw University of Surrey, Guildford, GU2 7XH P. Bianco
MagBeam: R. Winglee, T. Ziemba, J. Prager, B. Roberson, J Carscadden Coherent Beaming of Plasma. Separation of Power/Fuel from Payload
MagBeam: R. Winglee, T. Ziemba, J. Prager, B. Roberson, J Carscadden Coherent Beaming of Plasma Separation of Power/Fuel from Payload Fast, cost-efficient propulsion for multiple missions Plasma Propulsion
Cold Gas Thruster Qualification for FORMOSAT 5
Cold Gas Thruster Qualification for FORMOSAT 5 By Hans-Peter HARMANN 1), Tammo ROMBACH 2) and Heiko DARTSCH 1) 1) AST Advanced Space Technologies GmbH, Stuhr, Germany 2) SpaceTech GmbH, Immenstaad, Germany
YUsend-1 Solid Propellant Microthruster Design, Fabrication and Testing
YUsend-1 Solid Propellant Microthruster Design, Fabrication and Testing 24 th AIAA/USU Conference on Small Satellites Authors: Kartheephan Sathiyanathan, Regina Lee, Hugh Chesser (York University) Charles
Performance Improvement of Pulsed Plasma Thruster for Micro Satellite *
Performance Improvement of Pulsed Plasma Thruster for Micro Satellite * Miwa IGARASHI, Naoki KUMAGAI, Kensuke SATO, Kouji TAMURA and Haruki TAKEGAHARA Tokyo Metropolitan Institute of Technology Asahigaoka
A Regional Microsatellite Constellation with Electric Propulsion In Support of Tuscan Agriculture
Berlin, 20 th - 24 th 2015 University of Pisa 10 th IAA Symposium on Small Satellites for Earth Observation Student Conference A Regional Microsatellite Constellation with Electric Propulsion In Support
A novel pulsed plasma thruster design based on special capillary cavity structure IEPC
A novel pulsed plasma thruster design based on special capillary cavity structure IEPC-2017-428 Presented at the 35th International Electric Propulsion Conference Georgia Institute of Technology Atlanta,
Propellant Loading Effects on Ferroelectric Plasma Thruster Performance and Possible Applications
Propellant Loading Effects on Ferroelectric Plasma Thruster Performance and Possible Applications IEPC-29-177 Presented at the 31st International Electric Propulsion Conference, University of Michigan
Non-Phase-Difference Rogowski Coil for Measuring Pulsed Plasma Thruster Discharge Current
Non-Phase-Difference Rogowski Coil for Measuring Pulsed Plasma Thruster Discharge Current IEPC-2015-49/ISTS-2015-b-49 Presented at Joint Conference of 30th International Symposium on Space Technology and
Development of stationary plasma thruster SPT-230 with discharge power of kw
Development of stationary plasma thruster SPT-230 with discharge power of 10...15 kw IEPC-2017-548 Presented at the 35th International Electric Propulsion Conference Georgia Institute of Technology Atlanta,
Electric Propulsion Research and Development at NASA-MSFC
Electric Propulsion Research and Development at NASA-MSFC November 2014 Early NEP concept for JIMO mission Dr. Kurt Polzin (kurt.a.polzin@nasa.gov) Propulsion Research and Development Laboratory NASA -
Advancing the Utility of Small Satellites with the Development of a Hybrid Electric-Laser Propulsion (HELP) System
Advancing the Utility of Small Satellites with the Development of a Hybrid Electric-Laser Propulsion (HELP) System Dr. Rachel Leach, Gerry Murphy & Tom Adams Design_Net Engineering LLC August 12, 2004
µ-ppts diagnostics: a high accuracy impulsive thrust balance
µ-ppts diagnostics: a high accuracy impulsive thrust balance IEPC-13-165 Presented at the 33rd International Electric Propulsion Conference, The George Washington University Washington, D.C. USA S. Ciaralli
Analysis of Relative Motion of Collocated Geostationary Satellites with Geometric Constraints
www.dlr.de Chart 1 Analysis of Relative Motion of Collocated Geostationary Satellites with Geometric Constraints SFFMT2013, München F. de Bruijn & E. Gill 31 May 2013 www.dlr.de Chart 2 Presentation Outline
DISCHARGE CHARACTERISTICS OF A LASER-ASSISTED PLASMA THRUSTER
DISCHARGE CHARACTERISTICS OF A LASER-ASSISTED PLASMA THRUSTER Hideyuki Horisawa *, Masatoshi Kawakami *, Wun-Wei Lin *, Akira Igari *, and Itsuro Kimura # * Department of Aeronautics and Astronautics,
STUDY ON PLUME CHARACTERISTICS OF PULSED PLASMA THRUSTER *
STUDY ON PLUME CHARACTERISTICS OF PULSED PLASMA THRUSTER * Kentaro Kawahara, Naoki Kumagai, Kensuke Sato, Kohji Tamura, Takahiro Koide, Kenji Harima, Tadanori Fukushima, Haruki Takegahara # Tokyo Metropolitan
Applied Thermodynamics - II
Gas Turbines Sudheer Siddapureddy sudheer@iitp.ac.in Department of Mechanical Engineering Jet Propulsion - Classification 1. A heated and compressed atmospheric air, mixed with products of combustion,
APPT Propulsion System for Small Satellites
APPT Propulsion System for Small Satellites IEPC-2005-111 Presented at the 29 th International Electric Propulsion Conference, Princeton University, Nikolay N. Antropov * and Garry A. Popov (1)Research
AIR FORCE INSTITUTE OF TECHNOLOGY
Equation Chapter 1 Section 1 CONTAMINATION STUDY OF A MICRO PULSED PLASMA THRUSTER THESIS Ceylan Kesenek, 1 ST Lt, TUAF AFIT/GA/ENY/08-M03 DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY AIR FORCE INSTITUTE
Physics 24 Exam 2 March 18, 2014
Exam Total / 200 Physics 24 Exam 2 March 18, 2014 Printed Name: Rec. Sec. Letter: Five multiple choice questions, 8 points each. Choose the best or most nearly correct answer. 1. You need to store electrical
Satellite Components & Systems. Dr. Ugur GUVEN Aerospace Engineer (P.hD) Nuclear Science & Technology Engineer (M.Sc)
Satellite Components & Systems Dr. Ugur GUVEN Aerospace Engineer (P.hD) Nuclear Science & Technology Engineer (M.Sc) Definitions Attitude: The way the satellite is inclined toward Earth at a certain inclination
Physics For Scientists and Engineers A Strategic Approach 3 rd Edition, AP Edition, 2013 Knight
For Scientists and Engineers A Strategic Approach 3 rd Edition, AP Edition, 2013 Knight To the Advanced Placement Topics for C *Advanced Placement, Advanced Placement Program, AP, and Pre-AP are registered
An Architecture of Modular Spacecraft with Integrated Structural Electrodynamic Propulsion (ISEP)
NIAC 7 th Annual Meeting Tucson, Arizona October 18 th, 2006 An Architecture of Modular Spacecraft with Integrated Structural Electrodynamic Propulsion (ISEP) Nestor Voronka, Robert Hoyt, Brian Gilchrist,
Research and Development of Very Low Power Cylindrical Hall Thrusters for Nano-Satellites
Research and Development of Very Low Power Cylindrical Hall Thrusters for Nano-Satellites IEPC--39 Presented at the 3nd International Electric Propulsion Conference, Wiesbaden Germany Tomoyuki Ikeda, Kazuya
A review of plasma thruster work at the Australian National University
A review of plasma thruster work at the Australian National University IEPC-2015-90850 Presented at Joint Conference of 30th International Symposium on Space Technology and Science 34th International Electric
11.1 Survey of Spacecraft Propulsion Systems
11.1 Survey of Spacecraft Propulsion Systems 11.1 Survey of Spacecraft Propulsion Systems In the progressing Space Age, spacecrafts such as satellites and space probes are the key to space exploration,
Physics 196 Final Test Point
Physics 196 Final Test - 120 Point Name You need to complete six 5-point problems and six 10-point problems. Cross off one 5-point problem and one 10-point problem. 1. Two small silver spheres, each with
The division of energy sources and the working substance in electric propulsioncan determines the range of applicability of electro jet propulsion sys
Vacuum Arc thruster development for Horyu-4 satellite KaterynaAheieva, Shingo Fuchikami, Hiroshi Fukuda, Tatsuo Shimizu, Kazuhiro Toyoda, Mengu Cho Kyushu Institute of Technology1 N589502a@mail.kyutech.jp
P202 Practice Exam 2 Spring 2004 Instructor: Prof. Sinova
P202 Practice Exam 2 Spring 2004 Instructor: Prof. Sinova Name: Date: (5)1. How many electrons flow through a battery that delivers a current of 3.0 A for 12 s? A) 4 B) 36 C) 4.8 10 15 D) 6.4 10 18 E)
Development of a Two-axis Dual Pendulum Thrust Stand for Thrust Vector Measurement of Hall Thrusters
Development of a Two-axis Dual Pendulum Thrust Stand for Thrust Vector Measurement of Hall Thrusters Naoki Nagao, Shigeru Yokota, Kimiya Komurasaki, and Yoshihiro Arakawa The University of Tokyo, Tokyo,
BravoSat: Optimizing the Delta-V Capability of a CubeSat Mission. with Novel Plasma Propulsion Technology ISSC 2013
BravoSat: Optimizing the Delta-V Capability of a CubeSat Mission with Novel Plasma Propulsion Technology Sara Spangelo, NASA JPL, Caltech Benjamin Longmier, University of Michigan Interplanetary Small
5.12 The Aerodynamic Assist Trajectories of Vehicles Propelled by Solar Radiation Pressure References...
1 The Two-Body Problem... 1 1.1 Position of the Problem... 1 1.2 The Conic Sections and Their Geometrical Properties... 12 1.3 The Elliptic Orbits... 20 1.4 The Hyperbolic and Parabolic Trajectories...
Question 1. Question 2. Question 3
Question 1 Switch S in in the figure is closed at time t = 0, to begin charging an initially uncharged capacitor of capacitance C = 18.2 μf through a resistor of resistance R = 22.3 Ω. At what time (in
FLIGHT TESTING OF VOLUME-IONIZATION ION THRUSTERS ON METEOR SATELLITE
FLIGHT TESTING OF VOLUME-IONIZATION ION THRUSTERS ON METEOR SATELLITE Vladimir P. Khodnenko NPP Russian scientific and Research Institute of Electromechanics Moscow 101000, P.O. Box 496, Russia Phone:
PHY114 S11 Final Exam
PHY4 S Final Exam S. G. Rajeev May 4 0 7:5 pm to 9:5 pm PLEASE write your workshop number and your workshop leader s name at the top of your book, so that you can collect your graded exams at the workshop.
Knowledge Integration Module 1 Fall 2016
Knowledge Integration Module 1 Fall 2016 1 Basic Objective of KI-1: The knowledge integration module 1 or KI-1 is a vehicle to help you better grasp the commonality and correlations between concepts covered
BIRDY-T : Focus on propulsive aspects of an icubsat to small bodies of the solar system
BIRDY-T : Focus on propulsive aspects of an icubsat to small bodies of the solar system Gary Quinsac, PhD student at PSL Supervisor: Benoît Mosser Co-supervisors: Boris Segret, Christophe Koppel icubesat,
Numerical Calculation of Electrothermal Pulsed Plasma Thrusters by One-Dimensional Flowfield Model
Numerical Calculation of Electrothermal Pulsed Plasma Thrusters by One-Dimensional Flowfield Model IEPC-2017-108 Presented at the 35th International Electric Propulsion Conference Georgia Institute of
Basics of Network Theory (Part-I)
Basics of Network Theory (Part-I) 1. One coulomb charge is equal to the charge on (a) 6.24 x 10 18 electrons (b) 6.24 x 10 24 electrons (c) 6.24 x 10 18 atoms (d) none of the above 2. The correct relation
PLK VICWOOD K.T. CHONG SIXTH FORM COLLEGE Form Six Second Term Final Examination ( ) Physics A-Level Paper 1 Question/Answer Book A
05-06/F. 6 Final Exam/AL Physics/Paper 1/P.1 PLK VICWOOD K.T. CHONG SIXTH FORM COLLEGE Form Six Second Term Final Examination (2005-2006) A Physics A-Level Paper 1 Question/Answer Book A Time Allowed:
Pulsed Plasma Thruster Propulsion Technology for Small Satellite
Pulsed Plasma Thruster Propulsion Technology for Small Satellite Garry A. Popov, Nikolay N. Antropov Research Institute of Applied Mechanics and Electrodynamics, 4, Volokolamskoye shosse, Moscow, 125810,
Capacitors. Charging a Capacitor. Charge and Capacitance. L05: Capacitors and Inductors
L05: Capacitors and Inductors 50 Capacitors 51 Outline of the lecture: Capacitors and capacitance. Energy storage. Capacitance formula. Types of capacitors. Inductors and inductance. Inductance formula.
SPACE DEBRIS MITIGATION TECHNOLOGIES
SPACE DEBRIS MITIGATION TECHNOLOGIES Rob Hoyt Tethers Unlimited, Inc. The orbital debris population and its potential for continued rapid growth presents a significant threat to DoD, NASA, commercial,
The ResistoJet as a simple and cost-effective propulsion system for nano- and microsatellites
1st IAA Latin American Symposium on Small Satellites Advanced Technologies and Distributed Systems March 7-10, 2017 IAA-LA-13-03 The ResistoJet as a simple and cost-effective propulsion system for nano-
IAC-13,C4,P,44.p1,x17254 THE DYNAMIC OPERATON OF A HIGH Q EMDRIVE MICROWAVE THRUSTER. Roger Shawyer C.Eng. MIET. FRAeS. SPR Ltd UK
IAC-13,C4,P,44.p1,x1754 THE DYNAMIC OPERATON OF A HIGH Q EMDRIVE MICROWAVE THRUSTER Roger Shawyer C.Eng. MIET. FRAeS SPR Ltd UK sprltd@emdrive.com ABSTRACT The static operation of an EmDrive microwave
Physics 240 Fall 2005: Exam #3. Please print your name: Please list your discussion section number: Please list your discussion instructor:
Physics 240 Fall 2005: Exam #3 Please print your name: Please list your discussion section number: Please list your discussion instructor: Form #1 Instructions 1. Fill in your name above 2. This will be
MULTIPLE CHOICE. Choose the one alternative that best completes the statement or answers the question.
Exam Name MULTIPLE CHOICE. Choose the one alternative that best completes the statement or answers the question. 1) A jeweler needs to electroplate gold (atomic mass 196.97 u) onto a bracelet. He knows
ET-105(A) : PHYSICS. Show that only an infinitesimal rotation can be regarded as a vector.
No. of Printed Pages : 7 ET-105(A) B.Tech. Civil (Construction Management) / B.Tech. Civil (Water Resources Engineering) / BTCLEVI / BTMEVI / BTELVI / BTECVI / BTCSVI Term-End Examination June, 2017 ET-105(A)
Practice Exam 1. Necessary Constants and Equations: Electric force (Coulomb s Law): Electric field due to a point charge:
Practice Exam 1 Necessary Constants and Equations: Electric force (Coulomb s Law): Electric field due to a point charge: Electric potential due to a point charge: Electric potential energy: Capacitor energy:
ELECTRICITY AND MAGNETISM
ELECTRICITY AND MAGNETISM Chapter 1. Electric Fields 1.1 Introduction 1.2 Triboelectric Effect 1.3 Experiments with Pith Balls 1.4 Experiments with a Gold-leaf Electroscope 1.5 Coulomb s Law 1.6 Electric
Performance Evaluation of A High Energy Pulsed Plasma Thruster II
Performance Evaluation of A High Energy Pulsed Plasma Thruster II IEPC-2005-282 Presented at the 29 th International Electric Propulsion Conference, Princeton University, Hani Kamhawi *, NASA Glenn Research
You may not start to read the questions printed on the subsequent pages of this question paper until instructed that you may do so by the Invigilator.
NTURL SCIENCES TRIPOS Part I Saturday 9 June 2007 1.30 pm to 4.30 pm PHYSICS nswer the whole of Section and four questions from Sections B, C and D, with at least one question from each of these Sections.
Pulsed Plasma Thruster Systems for Spacecraft Attitude Control. R. J. Cassady~ N. J. Meckel~ and W. A. Hoskins Olin Aerospace Company, Redmond, W A
Pulsed Plasma Thruster Systems for Spacecraft Attitude Control R. J. Cassady~ N. J. Meckel~ and W. A. Hoskins Olin Aerospace Company Redmond W A R. M. Myers S. R. Oleson NYMA nc. NASA LeRC Cleveland OH
Electrospray Propulsion Systems for Small Satellites
Electrospray Propulsion Systems for Small Satellites Douglas Spence, Eric Ehrbar, Nate Rosenblad, Nate Demmons, Tom Roy, Samuel Hoffman, Dan Williams, Vlad Hruby Busek Co. Inc. 11 Tech Circle, Natick,
IV. Rocket Propulsion Systems. A. Overview
IV. Rocket Propulsion Systems A. Overview by J. M. Seitzman for AE 4451 Jet and Rocket Propulsion Seitzman Rocket Overview-1 Rocket Definition Rocket Device that provides thrust to a vehicle by accelerating
Mathematical Modeling of Liquid-fed Pulsed Plasma Thruster
Article Mathematical Modeling of Liquid-fed Pulsed Plasma Thruster Kaartikey Misra 1 Manipal Institute of Technology, Manipal-576104, India Email: Kaartikey.Misra@learner.manipal.edu/ ayush42@gmail.com
Fundamental Study of Laser Micro Propulsion Using Powdered-Propellant
Fundamental Study of Laser Micro Propulsion Using Powdered-Propellant IEPC-2007-230 Presented at the 30 th International Electric Propulsion Conference, Florence, Italy S. Yokoyama *, and H. Horisawa Tokai
Research and Development of Osaka Institute of Technology PROITERES Nano-Satellite Series with Electric Rocket Engines
Research and Development of Osaka Institute of Technology PROITERES Nano-Satellite Series with Electric Rocket Engines IEPC-2013-103 Presented at the 33rd International Electric Propulsion Conference,
Code No: RR Set No. 1
Code No: RR410209 Set No. 1 1. What are the gases mainly used in insulating medium at high pressures? Which is more suitable? Why? What about its dielectric strength? Explain. [16] 2. (a) Define time lags
CHAPTER 3 SATELLITES IN FORMATION FLYING
38 CHAPTER 3 SATELLITES IN FORMATION FLYING 3.1 INTRODUCTION The concept of formation flight of satellites is different from that of a satellite constellation. As defined by the NASA Goddard Space Flight
AQA Physics A-level Section 7: Fields and Their Consequences
AQA Physics A-level Section 7: Fields and Their Consequences Key Points Gravitational fields A force field is a region in which a body experiences a non-contact force. Gravity is a universal force acting
1. (a) Describe the difference between over-expanded, under-expanded and ideallyexpanded
Code No: R05322106 Set No. 1 1. (a) Describe the difference between over-expanded, under-expanded and ideallyexpanded rocket nozzles. (b) While on its way into orbit a space shuttle with an initial mass
Louisiana State University Physics 2102, Exam 2, March 5th, 2009.
PRINT Your Name: Instructor: Louisiana State University Physics 2102, Exam 2, March 5th, 2009. Please be sure to PRINT your name and class instructor above. The test consists of 4 questions (multiple choice),
PHYS 2135 Exam II March 20, 2018
Exam Total /200 PHYS 2135 Exam II March 20, 2018 Name: Recitation Section: Five multiple choice questions, 8 points each. Choose the best or most nearly correct answer. For questions 6-9, solutions must
UNIVERSITY OF CAMBRIDGE INTERNATIONAL EXAMINATIONS General Certificate of Education Advanced Level
UNIVERSITY OF CAMBRIDGE INTERNATIONAL EXAMINATIONS General Certificate of Education Advanced Level *2900417311* PHYSICS 9702/42 Paper 4 A2 Structured Questions October/November 2010 1 hour 45 minutes Candidates
INVESTIGATION OF PULSED PLASMA THRUSTERS FOR SPACECRAFT ATTITUDE CONTROL
IEPC-97-128 813 INVESTIGATION OF PULSED PLASMA THRUSTERS FOR SPACECRAFT ATTITUDE CONTROL N.J. Meckel, R.J. Cassady, R.D. Osborne, W.A. Hoskins, R.M. Myers PRIMEX Aerospace Company Redmond, WA. ABSTRACT
Switching to OCR from Pearson (Edexcel)
Switching to OCR from Pearson (Edexcel) The content within the OCR Physics A specification covers the Big Ideas of physics and will be very familiar. We ve laid it out in a logical progression to support
Motional Emf. OpenStax
OpenStax-CNX module: m42400 1 * Motional Emf OpenStax This work is produced by OpenStax-CNX and licensed under the Creative Commons Attribution License 3.0 Abstract Calculate emf, force, magnetic eld,
(1) 2 amp. (2) 1 amp. (3) 0.5 amp. (4) 1.25 amp.
1Ω + 4V 8Ω 3Ω 4Ω (1) 2 amp. (2) 1 amp. (3) 0.5 amp. (4) 1.25 amp. 8. Which is correct for inside charged sphere : (1) E 0, V = 0 (2) E=0, V= 0 (3) E 0, V 0 (4) E=0, V = 0 9. The magnetic force experienced
AP Physics C: Mechanics 2007 Free-Response Questions. The College Board: Connecting Students to College Success
AP Physics C: Mechanics 2007 Free-Response Questions The College Board: Connecting Students to College Success The College Board is a not-for-profit membership association whose mission is to connect students