BUILDING LOW-COST NANO-SATELLITES: THE IMPORTANCE OF A PROPER ENVIRONMENTAL TESTS CAMPAIGN. Jose Sergio Almeida INPE (Brazil)
|
|
- Curtis Hawkins
- 5 years ago
- Views:
Transcription
1 BUILDING LOW-COST NANO-SATELLITES: THE IMPORTANCE OF A PROPER ENVIRONMENTAL TESTS CAMPAIGN Jose Sergio Almeida INPE (Brazil) 1 st International Academy of Astronautics Latin American Symposium on Small Satellites: Advanced Technologies and Distributed Systems 7-10 March 2017 San Martin, Buenos Aires - Argentina LABORATÓRIO DE INTEGRAÇÃO E TESTES
2 The spacecraft may be: - Simplified in its design - Miniaturized in its size - significantly reduced in its total cost but the harsh of the launching stresses and the space environment of the orbit still remains virtually the same!
3 past few years: increase interest in very small satellites Possible from: miniaturization and better performance of electronic and some mechanical components also because of relatively lower costs associated to project, production and launching of these tiny spacecraft nano-satellites proved valuable for students opportunity of better understanding and learning details of design, construction, tests, launching and operating a real spacecraft also very useful in terms of low-cost platform for qualification, in orbital flight, of new technologies for space application
4 with typical low-budget, short time of design, construction and production significant risk of underestimating importance of environmental tests the spacecraft has to be submitted to increase probability of operational success during launching and orbital flight typically CubeSats and other relatively lower-cost nano-satellites make use of COTS components, and frequently include new kinds of payload equipment more attention and more severe ground environmental tests shall be recommended
5 The Vibration and Shock Environment Current launching vehicles are powered by solid boosters or liquid-injection operating engines, vigorous burning of fuel inducing significant levels of vibration in structural elements and equipment of spacecraft Also, the rocket high-speed crossing along atmosphere generates shock waves producing significant noise and vibration on top of tiny passenger spacecraft computer-based structural modelling to analyse that mechanicdesigned spacecraft will withstand and remain healthy and safe
6 But: Although computer modelling are producing more accurate output data, they are not perfect (and also depend on Engineer for correct inputs and data) Building materials, including metallic and structural parts, resins, fasteners etc. may not be produced exactly as theoretically proposed and expected Even with the well-qualified assembly and integration procedures, and even with proper training, the hand-operation of the technician can not guarantee that all the details of the procedure were executed exactly as programmed and expected So, the best way to confirm that it is ready for launch and orbital flight is submitting the hardware to real, actual laboratorial environmental tests
7 Nano-satellite instrumented with vibration sensors (accelerometers) able to read acceleration taking place at the location and direction(s), along the frequency sweeps Nano-satellite installed inside ejection device, all properly installed on top of the laboratory Shaker, accelerometer cables taken to a Data Acquisition System for real-time reading and recording for post analysis
8 The Environment of High-Vacuum and Temperature Extremes when spacecraft reaches orbital altitude it confronts with the high vacuum and soon with the temperature extremes of the space environment all materials that compose the spacecraft (metals, fibres, special painting, surface finishing, cabling etc.) shall be fully compatible in terms of material stability with the harsh of the very low pressure of the space environment If not compatible occurrence of outgassing phenomenon Outgassing: if gas releasing rate significant risk the material or component may change physical or chemical properties, possible degradation on its operational or functional demand within the spacecraft
9 The Environment of High-Vacuum and Temperature Extremes Traditionally, CubeSats tend to adopt COTS (Commercial Off-The-Shelf) components usually do not have the tight technical qualification for space application Usually they have lower costs and shorter delivery time when compared to their space-qualified counterparts Also, nano-satellites in many cases are launched into space as a second payload (piggy-back), together with high-cost large spacecraft significant additional concern in terms of chemical contamination from the nano-satellite to the main payload
10 The Environment of High-Vacuum and Temperature Extremes Outgassing rate verification under high vacuum conditioning: Spacecraft is put in a vacuum chamber, clean high-vacuum conditioning, mass spectrometer used to analyse, to identify and estimate the rate of any significant gas releasing from the spacecraft Bake-out Procedure: Spacecraft in a vacuum chamber, clean high-vacuum conditioning, warming up the whole satellite to tolerable high temperature, keep in the condition for a period of time (e.g. 24h or 48h). This accelerates releasing of gases from spacecraft, making it cleaner and more appropriate to be launched together with higher-costs satellites. Usually this is a call from the launch vehicle authorities.
11 The Environment of High-Vacuum and Temperature Extremes The issue of High and Low Temperatures Outside the atmosphere, when satellite is within Sun s sight, quite significant rate of solar radiation impinges its surfaces may generate significant amount of heat When the spacecraft goes to Earth eclipse mode spacecraft can lose heat, for small satellites this can take place in a very fast mode
12 The Environment of High-Vacuum and Temperature Extremes The issue of High and Low Temperatures Components adopted for nano-satellites (CubeSats) not necessarily are fully qualified to endure stress of high and low temperatures Recommended computer thermal modelling of spacecraft to optimize thermal design, aiming to moderate extremes of high and low temperature during orbital flight, in this way keeping it inside the operational temperature range.
13 But: The best computer-assisted thermal modelling of the satellite will not guarantee that: the thermal design and control will work perfectly and that the several parts of spacecraft will operate between safe extremes of temperature the spacecraft components and subsystems will operate accordingly and successfully when submitted to the high and low temperatures during the orbital flight The workmanship produced by technicians during assembling & integration (also involving thermal aspects and peculiarities), cannot be taken as exact the way it was specified in the procedures So, the best way to confirm that it is ready for orbital flight is submitting the hardware to real, actual laboratorial environmental tests
14 The Environment of High-Vacuum and Temperature Extremes Spacecraft instrumented with temperature sensors, quantity and location according to monitoring requirements Spacecraft installed in a thermal-vacuum chamber, all test cabling including any harness for functioning tests if the case, is connected to DAS or EGSE, chamber closed High vacuum conditioning, thermal shroud produce heat to warm-up spacecraft to hot-case condition where electrical functional tests can be performed on S/C Tvac chamber shrouds cooled down, by radiative heat transfer the S/C is also cooled down to specified cold-case condition where electrical functioning tests are performed on S/C. Depending on specification, more than one thermal cycle may be executed
15 The Environment of High-Vacuum and Temperature Extremes A nano-satellite being prepared for Thermal-Vacuum Tests
16 The Matter of Electromagnetic Compatibility Virtually all nano-satellites carry some kind of communication subsystem (send signal and/or data to ground stations, communication among other satellites for instance) Also, nano-satellites may carry sensitive on-board electromagnetic equipment To ensure the on-board equipment is safe against possible interferences, and also safe against players as the launching vehicle communication system or launcher main payload(s), computational electromagnetics simulations are performed But, still, tests related to possible electromagnetic interference are recommended to be executed in the Laboratory
17 The Matter of Electromagnetic Compatibility Emission Testing Nano-satellite positioned in Anechoic Chamber, put into operation and the levels and characteristics of the emitted electromagnetic waves are analysed to verify if they are within safe range. Susceptibility Testing Spacecraft positioned nearby a well-defined source of RF or electromagnetic pulse energy, so radiating antenna can direct energy at spacecraft, so measurements are performed to analyse the results in terms of how much it may be affected.
18 Mass Properties Measurements No spacecraft may be launched into space without precisely knowing its physical characteristics. This includes: measurement of its mass (M) centre of gravity location (C.G.) moment of inertia (MOI) and others These can be accomplished by using dedicated facilities provided by the testing laboratory Mass Properties Measurements of a nano-satellite give the spacecraft its characterization in terms of actual physical properties, absolutely mandatory for its launching campaign
19 Conclusion New technologies, lower-cost components and materials that may be typically connected to CubeSats may have significant probability of presenting some kind of premature malfunction Significant amount of time and resources shall absolutely be allocated in order to support and to assure a proper spacecraft environmental testing campaign If CubeSat is conceived inside the Academia, students naturally hold very high expectation to witness their space product operating accordingly in orbit. big frustration if happens a premature mal-function The bottom line: if the nano-satellite has to use components that do not hold full, proved, space qualification, so a higher reason that laboratory environmental tests are absolutely required, aiming to mitigate chances of failure
20 Conclusion Contrary to that many project managers may presume, lower-cost and perhaps simpler spacecraft definitely will require still more attention in terms of hardware qualification against the very tight stress of the launching and space environment, before it can be considered as ready to initiate its mission in space. Thank you for your attention!
THERMAL-VACUUM TESTS OF THE AMAZONIA-1 SATELLITE TM PERFORMED AT INPE WITH SUCCESS
IAC-16- C2,7,9,x33007 THERMAL-VACUUM TESTS OF THE AMAZONIA-1 SATELLITE TM PERFORMED AT INPE WITH SUCCESS Almeida, J. S.*., Panissi, D. L., Santos, M.B. National Institute for Space Research - INPE Sao
More informationThe time period while the spacecraft is in transit to lunar orbit shall be used to verify the functionality of the spacecraft.
ASE 379L Group #2: Homework #4 James Carlson Due: Feb. 15, 2008 Henri Kjellberg Leah Olson Emily Svrcek Requirements The spacecraft shall be launched to Earth orbit using a launch vehicle selected by the
More informationSpacecraft Structures
Tom Sarafin Instar Engineering and Consulting, Inc. 6901 S. Pierce St., Suite 384, Littleton, CO 80128 303-973-2316 tom.sarafin@instarengineering.com Functions Being Compatible with the Launch Vehicle
More informationSpace mission environments: sources for loading and structural requirements
Space structures Space mission environments: sources for loading and structural requirements Prof. P. Gaudenzi Università di Roma La Sapienza, Rome Italy paolo.gaudenzi@uniroma1.it 1 THE STRUCTURAL SYSTEM
More informationSTRUCTURAL MODELS AND MECHANICAL TESTS IN THE DEVELOPMENT OF A COMMUNICATIONS SPACECRAFT
First Pan American Congress on Computational Mechanics PANACM 2015 April 27-29, 2015, Buenos Aires, Argentina STRUCTURAL MODELS AND MECHANICAL TESTS IN THE DEVELOPMENT OF A COMMUNICATIONS SPACECRAFT Santiago
More informationPRACTICE NO. PD-ED-1259 PREFERRED May 1996 RELIABILITY PAGE 1 OF 6 PRACTICES ACOUSTIC NOISE REQUIREMENT
PREFERRED May 1996 RELIABILITY PAGE 1 OF 6 PRACTICES Practice: Impose an acoustic noise requirement on spacecraft hardware design to ensure the structural integrity of the vehicle and its components in
More informationDesign of Attitude Determination and Control Subsystem
Design of Attitude Determination and Control Subsystem 1) Control Modes and Requirements Control Modes: Control Modes Explanation 1 ) Spin-Up Mode - Acquisition of Stability through spin-up maneuver -
More informationAeolus ESA s Wind Lidar Mission: Technical Status & Latest Results
Aeolus ESA s Wind Lidar Mission: Technical Status & Latest Results Anders Elfving Project Manager European Space Agency/ESTEC Aeolus Cal/Val Workshop Meteo France, Toulouse, 28/03/2017 ESA UNCLASSIFIED
More informationNet Capture Mechanism for Debris Removal Demonstration Mission
Net Capture Mechanism for Debris Removal Demonstration Mission Robert Axthelm (1), Barbara Klotz (2), Dr. Ingo Retat (3), Uwe Schlossstein (4), Wolfgang Tritsch (5), Susanne Vahsen (6) Airbus DS, Airbus
More informationMake Your Cubesat Overnight and Put it in Any Orbit (Well almost)
Make Your Cubesat Overnight and Put it in Any Orbit (Well almost) Jim White, Walter Holemans, Planetary Systems Inc. Dr. Adam Huang, University of Arkansas RAMPART Summary Main Components The Promise of
More informationBepiColombo. Project and MPO Status. Comprehensive Explora1on of Planet Mercury
BepiColombo Project and MPO Status Comprehensive Explora1on of Planet Mercury Joe Zender BepiColombo Deputy PS, ESA/ESTEC BepiColombo Previously: Ø Proba2 Science Coordinator, until 12/2013 Ø ProbaV, Project
More informationPredicting Long-Term Telemetry Behavior for Lunar Orbiting, Deep Space, Planetary and Earth Orbiting Satellites
Predicting Long-Term Telemetry Behavior for Lunar Orbiting, Deep Space, Planetary and Earth Orbiting Satellites Item Type text; Proceedings Authors Losik, Len Publisher International Foundation for Telemetering
More informationCosmic Ray Telescope for the Effects of Radiation to Spacecraft Thermal Interface Control Document
Effective Date: 01/11/2007 Expiration Date: 01/11/2012 Lunar Reconnaissance Orbiter Project Cosmic Ray Telescope for the Effects of Radiation to Spacecraft Thermal Interface Control Document December 19,
More informationThe Quantum Sensor Challenge Designing a System for a Space Mission. Astrid Heske European Space Agency The Netherlands
The Quantum Sensor Challenge Designing a System for a Space Mission Astrid Heske European Space Agency The Netherlands Rencontres de Moriond - Gravitation, La Thuile, 2017 Quantum Sensors in Lab Experiments
More informationPREFERRED RELIABILITY PRACTICES. Practice:
PREFERRED RELIABILITY PRACTICES Practice No. PD-ED-1239 Page 1 of 6 October 1995 SPACECRAFT THERMAL CONTROL COATINGS DESIGN AND APPLICATION Practice: Select and apply thermal coatings for control of spacecraft
More informationDISTRIBUTION LIST. Others original copies Name amount. Lens Research & Development 1x Uittenhout, J.M.M. 1x DOCUMENT CHANGE RECORD
2 of 15 DISTRIBUTION LIST Others original copies Name amount Lens Research & Development 1x Uittenhout, J.M.M. 1x DOCUMENT CHANGE RECORD Issue Date Total pages Pages affected Brief description of change
More informationCosmic Ray Telescope for the Effects of Radiation to Spacecraft Thermal Interface Control Document
Effective Date: February 14, 2006 Expiration Date: February 14, 2011 Lunar Reconnaissance Orbiter Project Cosmic Ray Telescope for the Effects of Radiation to Spacecraft Thermal Interface Control Document
More informationSatellite 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
More informationMechanical and Thermal Design of XMM
r bulletin 100 december 1999 Mechanical and Thermal Design of XMM K. van Katwijk, T. van der Laan & D. Stramaccioni XMM Project, ESA Directorate for Scientific Programmes, ESTEC, Noordwijk, The Netherlands
More informationVibration Testing of Small Satellites
Vibration Testing of Small Satellites This series of papers provides a tutorial along with guidelines and recommendations for vibration testing of small satellites. Our aim with these papers is to help
More informationPrecision Attitude and Translation Control Design and Optimization
Precision Attitude and Translation Control Design and Optimization John Mester and Saps Buchman Hansen Experimental Physics Laboratory, Stanford University, Stanford, California, U.S.A. Abstract Future
More informationPRACTICE NO. PD-AP-1309 PREFERRED PAGE 1 OF 5 RELIABILITY PRACTICES ANALYSIS OF RADIATED EMI FROM ESD EVENTS CAUSED BY SPACE CHARGING
PREFERRED PAGE 1 OF 5 RELIABILITY PRACTICES ANALYSIS OF RADIATED EMI FROM ESD EVENTS Practice: Modeling is utilized for the analysis of conducted and radiated electromagnetic interference (EMI) caused
More informationPuerto Rico CubeSat NanoRock2 PR-CuNaR2
Puerto Rico CubeSat NanoRock2 PR-CuNaR2 Dr. Amilcar Rincon-Charris Mechanical Engineering Department 2018 Outline Introduction PR-CuNaR2 Components Avionics and Payload Facilities Future work http://bayamon.inter.edu
More informationBEOSAT (BRUNSWICK-EARTH-OBSERVATION-SATELLITE)
ABSTRACT BEOSAT (BRUNSWICK-EARTH-OBSERVATION-SATELLITE) Rolf Kluge Jörn Pfingstgräff ExperimentalRaumfahrt-InteressenGemeinschaft e.v., Germany r.kluge@tu-braunschweig.de j.pfingstgraeff@tu-braunschweig.de
More informationALCATEL SPACE PLASMA PROPULSION SUBSYSTEM QUALIFICATION STATUS
ALCATEL SPACE PLASMA PROPULSION SUBSYSTEM QUALIFICATION STATUS Pascal GARNERO, Olivier DULAU ALCATEL SPACE 100, Bd. du Midi, BP 99 06156 CANNES LA BOCCA Cedex FRANCE Contact : pascal.garnero@space.alcatel.fr,
More informationSPACE 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,
More informationLAUNCH SYSTEMS. Col. John Keesee. 5 September 2003
LAUNCH SYSTEMS Col. John Keesee 5 September 2003 Outline Launch systems characteristics Launch systems selection process Spacecraft design envelope & environments. Each student will Lesson Objectives Understand
More informationStellarXplorers IV Qualifying Round 2 (QR2) Quiz Answer Key
1. Which of these Electromagnetic radiation bands has the longest wavelength (λ)? [Section 12.1] a. X-Ray b. Visible Light c. Infrared d. Radio 2. How is energy in Electromagnetic (EM) radiation related
More information4.8 Space Research and Exploration. Getting Into Space
4.8 Space Research and Exploration Getting Into Space Astronauts are pioneers venturing into uncharted territory. The vehicles used to get them into space are complex and use powerful rockets. Space vehicles
More informationTHE MICRO ADVANCED STELLAR COMPASS FOR ESA S PROBA 2 MISSION
THE MICRO ADVANCED STELLAR COMPASS FOR ESA S PROBA 2 MISSION P.S. Jørgensen (1), J.L. Jørgensen (1), T. Denver (1), Pieter van den Braembuche (2) (1) Technical University of Denmark, Ørsted*DTU, Measurement
More informationADM-Aeolus Science and Cal/Val Workshop
ADM-Aeolus Science and Cal/Val Workshop ESA ESRIN, Frascati, ITALY 10 13 February 2015 THE ALADIN INSTRUMENT AND ITS ON-GROUND CHARACTERISATION O. Lecrenier, F. Fabre, J. Lochard Airbus Defense & Space
More informationMISSION ENGINEERING SPACECRAFT DESIGN
MISSION ENGINEERING & SPACECRAFT DESIGN Alpbach 2007 - D.J.P. Moura - CNES MISSION ENGINEERING (1) OVERALL MISSION ENGINEERING IS A COMPLEX TASK SINCE AT THE BEGINNING THE PROBLEM IS GENERALLY BADLY EXPRESSED
More informationTESTIMONY BEFORE. HOUSE CO1MfITTEE ON SCIENCE AND ASTRONAUTICS SUBCOWITTEE ON SPACE SCIENCES AND APPLICATIONS. Dr. John W.
October 9, 1973 TESTIMONY BEFORE HOUSE CO1MfITTEE ON SCIENCE AND ASTRONAUTICS SUBCOWITTEE ON SPACE SCIENCES AND APPLICATIONS Dr. John W. Findlay Chairman Space Science Board Suumer Study SCIENTIFIC USES
More informationDRAFT. Robotic Lunar Exploration Program Lunar Reconnaissance Orbiter 431-ICD Date: September 15, 2005
DRAFT Robotic Lunar Exploration Program Lunar Reconnaissance Orbiter Lunar Reconnaissance Orbiter to Comic Ray Telescope for the Effects of Radiation Mechanical Interface Control Document Date: September
More information12.3 Exploring Space: Past, Present and Future
12.3 Exploring Space: Past, Present and Future Until the invention of the telescope, knowledge of space was very weak, and mythology and speculation were the rule. The telescope was invented in the 17th
More informationThe E-SAIL programme. 10th IAA Symposium on Small Satellites for Earth Observation April 20-24, 2015 Berlin LuxSpace s.à.r.
The E-SAIL programme 10th IAA Symposium on Small Satellites for Earth Observation April 20-24, 2015 Berlin LuxSpace s.à.r.l An OHB company Contents LuxSpace Background Consortium Spacecraft Specific issues
More informationAeolus ESA s Wind Lidar Mission: Objectives, Design & Status
Aeolus ESA s Wind Lidar Mission: Objectives, Design & Status Anne Grete Straume on behalf of Anders Elfving European Space Agency/ESTEC Working Group on Space-based Lidar Winds Boulder, 28/04/2015 Atmospheric
More informationTHERMAL DESIGN OF SACI-1 SATELLITE
THERMAL DESIGN OF SACI-1 SATELLITE Issamu Muraoka - issamu@dem.inpe.br INPE - Instituto Nacional de Pesquisas Espaciais Av. dos Astronautas, 1758 - São José dos Campos - SP- Brazil Abstract. This paper
More informationNovember 3, 2014 Eric P. Smith JWST Program Office
November 3, 014 Eric P. Smith JWST Program Office 1 SINCE LAST CAA MEETING... Completed of 3 recommended GAO schedule risk analyses for this year. Mutually agreed to drop 3 rd. Will perform cost-risk study
More informationThe Interstellar Boundary Explorer (IBEX) Mission Design: A Pegasus Class Mission to a High Energy Orbit
The Interstellar Boundary Explorer (IBEX) Mission Design: A Pegasus Class Mission to a High Energy Orbit Ryan Tyler, D.J. McComas, Howard Runge, John Scherrer, Mark Tapley 1 IBEX Science Requirements IBEX
More informationStatus / Progress of the erosita X ray Observatory:
Status / Progress of the erosita X ray Observatory: Vadim Burwitz, Max Planck Institut für extraterrestrische Physik On behalf of the erosita Team IACHEC #9, May 13, 2014, Airlie Center, Warrenton, Virginia,
More informationGOSAT MISSION and SPACECRAFT PARTS REQUIRMENTS
MISSION and SPACECRAFT PARTS REQUIRMENTS OCT. 22, 2004 GOSAT PROJECT TEAM Japan Aerospace Exploration Agency (JAXA) GOSAT Objectives (1) Kyoto Protocol (1997): Mandatory for Developed Nations to Reduce
More informationLaunch Environment. Phase C. Date : 06/03/2008 Issue : 1 Rev : 6 Page : 1 of 23. Prepared by: Guillaume Roethlisberger. Checked by: Approved by:
Page : 1 of 23 Phase C Launch Environment Prepared by: Guillaume Roethlisberger Checked by: Approved by: EPFL Lausanne Switzerland 06/03/2008 Page : 2 of 23 RECORD OF REVISIONS ISS/REV Date Modifications
More informationA 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
More informationCreating Large Space Platforms From Small Satellites
SSC99-VI-6 Creating Large Space Platforms From Small Satellites Andrew W. Lewin Principal Systems Engineer Orbital Sciences Corporation Dulles, VA 20166 (703) 406-5000 lewin.andy@orbital.com Abstract.
More informationTime and Frequency Activities at the JHU Applied Physics Laboratory
Time and Frequency Activities at the JHU Applied Physics Laboratory Mihran Miranian, Gregory L. Weaver, Jeffrey F. Garstecki, and Richard A. Dragonette Johns Hopkins University Applied Physics Laboratory,
More informationA Concept of Nanosatellite Small Fleet for Earth Observation
A Concept of Nanosatellite Small Fleet for Earth Observation Prof. Janusz Narkiewicz jnark@meil.pw.edu.pl Sebastian Topczewski stopczewski@meil.pw.edu.pl Mateusz Sochacki msochacki@meil.pw.edu.pl 10-11
More informationMAE 180A: Spacecraft Guidance I, Summer 2009 Homework 4 Due Thursday, July 30.
MAE 180A: Spacecraft Guidance I, Summer 2009 Homework 4 Due Thursday, July 30. Guidelines: Please turn in a neat and clean homework that gives all the formulae that you have used as well as details that
More informationPROBA 1. F. Teston ESA/ESTEC D/TEC-EL
PROBA 1 F. Teston ESA/ESTEC D/TEC-EL Frederic.Teston@esa.int PROBA 1 launch PROBA 1 has been launched on 21 October 2001 Orbital parameters: Altitude: 681-561 km Near polar (inclination of 97.9 ) Sun-synchronous
More informationLOW-COST LUNAR COMMUNICATION AND NAVIGATION
LOW-COST LUNAR COMMUNICATION AND NAVIGATION Keric Hill, Jeffrey Parker, George H. Born, and Martin W. Lo Introduction Spacecraft in halo orbits near the Moon could relay communications for lunar missions
More informationLunar Flashlight Project
ABSTRACT Recent observations of the Moon with the Moon Mineralogy Mapper (M3), Lunar Crater Observation and Sensing Satellite (LCROSS), the Lunar Reconnaissance Orbiter (LRO) and other evidence suggest
More informationVIRTUAL TESTING SIMULATION TOOL FOR THE NEW QUAD HEAD EXPANDER ELECTRODYNAMIC SHAKER
VIRTUAL TESTING SIMULATION TOOL FOR THE NEW QUAD HEAD EXPANDER ELECTRODYNAMIC SHAKER Matteo Appolloni,* AOES BV Alessandro Cozzani, European Space Agency * Matteo.Appolloni@esa.int Outline Introduction
More informationElectric Propulsion System using a Helicon Plasma Thruster (2015-b/IEPC-415)
Electric Propulsion System using a Helicon Plasma Thruster (2015-b/IEPC-415) Presented at Joint Conference of 30th International Symposium on Space Technology and Science 34th International Electric Propulsion
More informationSystem engineering approach toward the problem of required level of in-orbit autonomousoperation of a LEO microsatellite mission
System engineering approach toward the problem of required level of in-orbit autonomousoperation of a LEO microsatellite mission H.Bonyan Amirkabir University of Technology (AUT) H.Bonyan@dena.aut.ac.ir
More informationDARE Mission and Spacecraft Overview
DARE Mission and Spacecraft Overview October 6, 2010 Lisa Hardaway, PhD Mike Weiss, Scott Mitchell, Susan Borutzki, John Iacometti, Grant Helling The information contained herein is the private property
More informationBepiColombo Project Status. Presentation for MESSENGER Science Team Meeting Via-Skype, 27 th March 2015
BepiColombo Project Status Johannes.Benkhoff@esa.int Presentation for MESSENGER Science Team Meeting Via-Skype, 27 th March 2015 Project status The purpose of this presentation is to give an overview on
More informationMULTI PURPOSE MISSION ANALYSIS DEVELOPMENT FRAMEWORK MUPUMA
MULTI PURPOSE MISSION ANALYSIS DEVELOPMENT FRAMEWORK MUPUMA Felipe Jiménez (1), Francisco Javier Atapuerca (2), José María de Juana (3) (1) GMV AD., Isaac Newton 11, 28760 Tres Cantos, Spain, e-mail: fjimenez@gmv.com
More informationUpdate on the In-orbit Performances of GIOVE Clocks
Update on the In-orbit Performances of GIOVE Clocks Pierre Waller, Francisco Gonzalez, Stefano Binda, ESA/ESTEC Ilaria Sesia, Patrizia Tavella, INRiM Irene Hidalgo, Guillermo Tobias, GMV Abstract The Galileo
More informationIntegrated Test Facility for Nanosat Assessment and Verification
Integrated Test Facility for Nanosat Assessment and Verification Steve Wassom, Quinn Young, Bryan Bingham, Rees Fullmer, Mitch Whiteley, Robert Burt, Mike Watson, Tom Ortiz, Joe Richards, Sam Wilcox Utah
More informationToshinori Kuwahara*, Yoshihiro Tomioka, Yuta Tanabe, Masato Fukuyama, Yuji Sakamoto, Kazuya Yoshida, Tohoku University, Japan
Toshinori Kuwahara*, Yoshihiro Tomioka, Yuta Tanabe, Masato Fukuyama, Yuji Sakamoto, Kazuya Yoshida, Tohoku University, Japan The 3 rd Nano-Satellite Symposium Micro/Nano Satellite & Debris Issues December
More informationThe 2013 MAVEN Mission To Mars. Bruce Jakosky MAVEN Principal Investigator University of Colorado
The 2013 MAVEN Mission To Mars Bruce Jakosky MAVEN Principal Investigator University of Colorado Summary of MAVEN Status We ve been developing MAVEN since 2003; now under 3 months to launch! All science
More informationOrbital Debris Mitigation
Orbital Debris Mitigation R. L. Kelley 1, D. R. Jarkey 2, G. Stansbery 3 1. Jacobs, NASA Johnson Space Center, Houston, TX 77058, USA 2. HX5 - Jacobs JETS Contract, NASA Johnson Space Center, Houston,
More informationAEROTHERMODYNAMIC ANALYSIS OF INNOVATIVE HYPERSONIC DEPLOYABLE REENTRY CAPSULES. Raffaele Savino University of Naples Federico II
AEROTHERMODYNAMIC ANALYSIS OF INNOVATIVE HYPERSONIC DEPLOYABLE REENTRY CAPSULES Raffaele Savino University of Naples Federico II Objectives Show the main capabilities of deployable aero-brakes for Earth
More informationHORYU-4: Miniaturised Laboratory for In-Orbit High Voltage Technology Demonstration Tatsuo Shimizu, HORYU-4 Project, Mengu Cho Kyushu Institute of Tec
HORYU-4: Miniaturised Laboratory for In-Orbit High Voltage Technology Demonstration Tatsuo Shimizu, HORYU-4 Project, Mengu Cho Kyushu Institute of Technology, 1-1 Sensui, Tobata, Kitakyushu, Fukuoka, Japan
More informationHigh Altitude Extremophiles. Request For Proposal
High Altitude Extremophiles Request For Proposal 14 February 2006 Submitted by: Team Phoenix Submitted to: Professor Koehler Phoenix - 1-2/24/2006 Mission Statement: Our primary mission is to create a
More information9 Aug 04 Getting Technology to Space for the Warfighter
1 SMC Detachment 12 - The Dirty Dozen Space Test Program-1 (STP-1) First of its Kind! Major Ray Galik STP-1 Program Manager 9 Aug 2004 Overview STP-1 Mission summary STP-1 Firsts Manifest Changes Space
More informationRemote Sensing. RAHS C Division Invitational
Remote Sensing RAHS C Division Invitational 2017-18 Instructions: Answer all questions on this answer sheet. Sheets may be double sided, check both sides! If you separate the sheets of the test be sure
More informationThermal Vacuum Test: Plans and Procedures
GLAST Large Area Telescope Gamma-ray Large Area Space Telescope Pre-Shipment Review Thermal Vacuum Test: Plans and Procedures Jesse Armiger Thermal Vacuum Test Director Thermal Vacuum Test Stanford Linear
More informationLunar Reconnaissance Orbiter Project. Cosmic Ray Telescope for the Effects of Radiation to Spacecraft Mechanical Interface Control Document
Revision B DraftA Effective Date: July 17, 2006 Expiration Date: July 17, 2011 Lunar Reconnaissance Orbiter Project Cosmic Ray Telescope for the Effects of Radiation to Spacecraft Mechanical Interface
More informationPico-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
More informationMarlene H. Dortch Secretary, Federal Communications Commission th Street, S.W. Washington, D.C
1776 K STREET NW WASHINGTON, DC 20006 PHONE 202.719.7000 November 10, 2016 Jennifer D. Hindin 202.719.4975 JHindin@wileyrein.com www.wileyrein.com VIA IBFS Marlene H. Dortch Secretary, Federal Communications
More informationDRAFT. Robotic Lunar Exploration Program Lunar Reconnaissance Orbiter (LRO)
DRAFT Robotic Lunar Exploration Program Lunar Reconnaissance Orbiter (LRO) Comic Ray Telescope for the Effects of Radiation (CRaTER) to Spacecraft Mechanical Interface Control Document Date: July 13, 2005
More informationWhen Going Live Means Launch, Literally: Quality Assurance Impressions From the Space Domain. Martin Jüssi AS CGI Eesti
When Going Live Means Launch, Literally: Quality Assurance Impressions From the Space Domain Martin Jüssi AS CGI Eesti Contents About myself Introduction to Space: Space Environment and Hazards Risk Management
More informationSPD QM Thermal Vacuum Testing
SPD 10003 QM Thermal Vacuum Testing Document Author(s): Seongwhan Lee swhan@khu.ac.kr Responsible Engineer(s): Seongwhan Lee Jungho Lee swhan@khu.ac.kr overthewater@khu.ac.kr Page 1/23 Revision History
More information5th Annual CubeSat Developers' Workshop April 2008 Cal Poly San Luis Obispo, California
5th Annual CubeSat Developers' Workshop 9-11 April 2008 Cal Poly San Luis Obispo, California From UNISAT to ubesatsat UNICube Chantal CAPPELLETTI, Fabrizio PAOLILLO, Francesco GUARDUCCI, Luigi RIDOLFI
More informationAIR BEARING ADCS TEST BED. Daniel E. Wukelic College of Engineering University of Hawai i at Mānoa Honolulu, HI ABSTRACT INTRODUCTION
AIR BEARING ADCS TEST BED Daniel E. Wukelic College of Engineering University of Hawai i at Mānoa Honolulu, HI 96822 ABSTRACT The Hawai i Space Flight Laboratory (HSFL) designs, tests and builds small
More informationObserving Convection in Microgravity. Matt Heer. East Troy High School Physics
Observing Convection in Microgravity Matt Heer East Troy High School Physics Abstract. The purpose of the experiment is to observe the movement, or lack thereof, of heat in an enclosed space in multiple
More informationTHERMAL CONTROL SUBSYSTEM
THERMAL CONTROL SUBSYSTEM Thermal Mission PDR Jeff Asher Los Angeles, California February 12, 2015 Thermal-1 MPDR, 2/12/2015 SUBSYSTEM TEAM Name Jeff Asher Ken Shrivastava Renee Krieger Chris Knapp Responsibility
More informationAnnouncement of Opportunity AKARI (ASTRO-F)
Announcement of Opportunity AKARI (ASTRO-F) CALL FOR OBSERVING PROPOSALS for the AKARI Post-Helium (phase 3) mission 2 nd year of Operations (October 2009 October 2010) Policies and procedures 27 May 2009
More informationCommunication. Provides the interface between ground and the spacecraft Functions:
Telecomm Communication Provides the interface between ground and the spacecraft Functions: Lock onto the ground station signal (carrier tracking) Receive uplink and process it (command reception and detection)
More informationCOMMUNICATION TEAM. You will be the only verbal link between Mars Control and the spacecraft for many of the teams!
COMMUNICATION TEAM Congratulations! You have been selected to be a mission specialist on the Communication Team. Your team s mission will be to establish a verbal link between Mars Control and the spacecraft.
More informationTest of the Qualification Model of UG electronics for the AMS TRD Gas System
Test of the Qualification Model of UG electronics for the AMS TRD Gas System Bruno Borgia, Alessandro Bartoloni, Francesca R. Spada April, 9 AMS Roma / rev. Contents Introduction. The UG-crate................................
More informationINTRODUCTION. Simple electron emitters for space. Simple mechanism of electron emission. Demand for electron sources in space
R E S E A R C H INTRODUCTION Simple electron emitters for space Demand for electron sources in space Asteroid explorer "Hayabusa" returned to Earth on June 13, 2010 after a seven-year space flight using
More informationDevelopment of Magnetometer and Sun Sensors Based Orbit and Attitude Determination for Cubesat
Development of Magnetometer and Sun Sensors Based Orbit and Attitude Determination for Cubesat MTS-UFS-CONAE Maria Pereyra, Roberto Alonso and Jose Kuba 1st IAA Latin American Symposium on Small Satellites
More informationCHAPTER 3 PERFORMANCE
PERFORMANCE 3.1 Introduction The LM-3B performance figures given in this chapter are based on the following assumptions: Launching from XSLC (Xichang Satellite Launch Center, Sichuan Province, China),
More informationGUIDANCE, NAVIGATION, AND CONTROL TECHNIQUES AND TECHNOLOGIES FOR ACTIVE DEBRIS REMOVAL
GUIDANCE, NAVIGATION, AND CONTROL TECHNIQUES AND TECHNOLOGIES FOR ACTIVE DEBRIS REMOVAL Antonio Rinalducci, Guillermo Ortega Hernando, Sven Erb, Alexander Cropp, Thomas Voirin, Olivier Dubois-Matra, Gianfranco
More informationPropulsion 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
More informationReport of the Venera-D Joint Science Definition Team: "Together to Venus"
Report of the Venera-D Joint Science Definition Team: "Together to Venus" L. Zasova1, D. Senske2, T. Economou3, N. Eismont1, L. Esposito4, M. Gerasimov1, N. Ignatiev1, M. Ivanov5, I. Khatuntsev1, O. Korablev1,
More informationCold 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
More informationAN OVERVIEW OF THE E.C.S.S. HANDBOOK FOR SPACECRAFT LOADS ANALYSIS
COMPDYN 2011 III ECCOMAS Thematic Conference on Computational Methods in Structural Dynamics and Earthquake Engineering M. Papadrakakis, M. Fragiadakis, V. Plevris (eds.) Corfu, Greece, 25 28 May 2011
More informationEnd of Life Re-orbiting The Meteosat-5 Experience
End of Life Re-orbiting The Meteosat-5 Experience Milan EUMETSAT, Darmstadt, Germany This article illustrates the orbit maneuver sequence performed during Meteosat- 5 End of Life (EOL) re-orbiting operations
More informationThe post launch assessment review confirmed the following previous assertions about the mission status:
1 GRACE Newsletter No. 2 August 15, 2003 Topics: http://www.csr.utexas/grace/ http://www.gfz-potsdam.de/grace 1. Editorial 2. Major events in Mission Operations since last Newsletter 3. Current status
More informationA 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
More informationThe 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
More informationModular Thermal Design Concepts: Thermal Design of a Spacecraft on a Module Level for LEO Missions
Modular Thermal Design Concepts: Thermal Design of a Spacecraft on a Module Level for LEO Missions Mark Barton AeroAstro mark.barton@aeroastro.com 703.723.9800 x 131 2005 AIAA/USU Conference on Small Satellites
More informationThe Challenge is to Define: System Engineering. System Engineering Components. Functional Requirements
The Challenge is to Define: System Engineering What it is supposed to do How well it must do it It s constituant parts and how they play together We are not prepared for detail design, assembly and test
More informationAeolus. A Mission to Map the Winds of Mars. Anthony Colaprete Amanda Cook NASA Ames Research Center
Aeolus A Mission to Map the Winds of Mars Anthony Colaprete Amanda Cook NASA Ames Research Center Low-Cost Planetary Missions Conference 12, 2017 What is Aeolus? Science Aeolus will provide the very first
More informationSOLAR FURNACE. By Heiko Ritter JOURNEY TO THE INNER
SOLAR FURNACE 88 Seite 1 By Heiko Ritter JOURNEY TO THE INNER THERMAL TESTS FOR Seite 2 SOLAR SYSTEM B E P I C O L O M B O T he European Space Agency, ESA, is currently developing a mission to the planet
More informationLeonid Meteor Observer in LEO: A Proposal for a University Microsatellite for the 2001 Leonids
Leonid Meteor Observer in LEO: A Proposal for a University Microsatellite for the 2001 Leonids Kazuya Yoshida* Hajime Yano** *Tohoku University **Institute of Space and Astronautical Science (ISAS) JAPAN
More informationPolish Student Activities in Space Research and Education
Polish Student Activities in Space Research and Education Warsaw University of Technology: Student Astronautical Group Student Space Engineering Scientific Group Radiolocation and Digital Signal Processing
More information