SAMPLE CANISTER CAPTURE MECHANISM FOR MSR: CONCEPT DESIGN AND TESTING RESULTS INCLUDING 0-G ENVIRONMENT
|
|
- Kelly Parsons
- 5 years ago
- Views:
Transcription
1 SAMPLE CANISTER CAPTURE MECHANISM FOR MSR: CONCEPT DESIGN AND TESTING RESULTS INCLUDING 0-G ENVIRONMENT Authors: Riccardo Carta, Daniele Filippetto, Politecnico di Milano Co-authors: Prof. Michèle Lavagna, Politecnico di Milano Mr. Filippo Mailland, CGS S.p.A. Dr Peter Falkner, ESA Mr Jonan Larranaga, Aurora Technology B.V. for ESA ASTRA 2015, Noordwijk, The Netherlands, 11 May 2015
2 Presentation Outline 2 1. Introduction to SCCM study 2. SCCM breadboard Manufacturing, Assembly, Integration and Test (MAIT) I. Manufacturing Assembly and Integration II. Test Plan and test facility III. Test results a. Functional Tests b. Thermal Vacuum Tests (TVT) c. Vibration Test (VT) 3. SCCM Parabolic Flight experiment I. Introduction II. Experiment Design III. Test Plan IV. Results 4. Conclusions
3 Mars Sample Return (MSR) architecture 3
4 Study Overview 4 Objectives: The Sample Canister Capture Mechanism (SCCM) is a feasibility Study to develop a technology concepts for a future Mars Sample Return (MSR) mission The SCCM will be in charge of capturing and securing an Orbiting Sample (OS) which accommodates the Martian soil samples Main goals of the Study: Build the Elegant Breadboard Model (EBM) Functional/ Environmental tests for TRL-4 Parabolic flight campaign for TRL-6
5 Study Critical Requirements 5 6 kg spherical OS: 230 mm diameter, Incoming relative velocity: 5-15 cm/s Angular misalignment: ±5 Radial offset: 10 cm Whole capture procedure within 90s Retention within 7 s Maximum stowed envelope 800 x 800 x 500 mm First natural frequency higher than 100 Hz Single point failure tolerance
6 Elegant Breadboard Model Design 6 EBM assembly Arm Hinge CAM Funnel Baseplate Support Tower Motor End Rotation Sensors Shims
7 High Level Test Plan 7 Test Plan Functional Tests Environmental Tests Thermal Vacuum Tests Mechanical Tests (Vibration)
8 Ground Test Objectives 8 Type of Test Test Article Test Objective Test facility Arm actuation functionalities Hold Down Release Mechanism functionality Functional Tests EBM OS detection Actuation chain performances Polimi (Including 0g GSE & OS Mockup) Motorization Factors assessment Motor Maximum Torque Estimation Thermal- Vacuum Tests EBM (excl. OS Mockup) EBM functionality at expected operative thermal conditions EBM survival at the expected non operative thermal conditions Serms srl Vibration test EBM (excl. OS Mockup) EBM withstanding of expected vibration levels Serms srl
9 Functional Test: Test Facility 9 Criticalities: OS swinging motion Funnel-OS position accuracy Requirement drivers: Cost Reusability Functionality Motorization factor EBM configuration PoliMi-DAST
10 Functional test 10 Functional tests results Test Article Test Objective Deployment Maximum torque Test Results Successful Duration: 17,70 17,84 s Successful Measured values: 10,85 10,94 Nm EBM Motorization factors Closure and reset Retention Successful Measured values: 60,28 60,68 Successful Duration: 17,61 18,15 s Successful Duration: 6,60 7,60 s Sensor failure simulation of test case 25/26 results in test failure
11 Environmental Test: Thermal-vacuum, cycles details 11 Temperature Minimum Non-Operational/Survival Temperature Minimum Operational Temperature Maximum Operational Temperature Maximum Non-Operational/Survival Temperature Values 248 K 252 K 322 K 335 K
12 Environmental Test: Thermal-vacuum, test facility 12 Thermal-vacuum chamber Thermocouples location
13 Thermal-vacuum tests 13 Funnel and Motor case temperature profile Temperature ( C) Time (min) Funnel Motor
14 Environmental Test: Vibration, Test Plan Details 14 # Run Test type Initial Conditions Characteristics 1 Resonance search test SCCM EBM in stowed configuration, not operative Band Hz Level: 0.2 g (Peak) 2 Sine vibration test X and Y axes SCCM EBM in stowed configuration, not operative Frequency 5 21 Hz ±5.7 mm Frequency Hz 10 g (*) Frequency Hz 6 g 2 Sine vibration test Z-axis SCCM EBM in stowed configuration, not operative Frequency 5 21 Hz ±11 mm Frequency Hz 20 g Frequency Hz 6 g 3 Random vibration test X and Y axes SCCM EBM in stowed configuration, not operative 9,03 g RMS 3 Random vibration test Z-axis SCCM EBM in stowed configuration, not operative 14,00 g RMS (*) Limit imposed by test facility equipment
15 Environmental Test: Vibration, test facility 15 Slip table Sensor MP15 MP17 MP20 MP21 MP23 MP31 MP42 MP65 Location Baseplate (Tower) Baseplate (Funnel) Arm tip Funnel top Arm shaft Lug top HDRM/arm Motor flange Shaker + head expander
16 Vibration tests 16 Resonance search results Mode ID FEM analysis [Hz] Before vibration test [Hz] (Reduction %) After vibration test [Hz] (Reduction %) (13.5%) 107 (13.5%) (12.8%) 117 (12.8%) (11.7%) 125 (11.7%) (8.1%) 136 (9.4%) (4.1%) 144 (4.8%) (10.4%) 201 (10.0%) 1 natural frequency higher than 100 Hz as required FEM increases stiffness Reduction percentage <15%
17 Parabolic Flight 17 ECSS standards for TRL-6 Testing full scale in relevant environment Microgravity operations Relative dynamics funnel-os OS capture operations Impact forces Aircraft manoeuvre allowing simulate weightlessness About 20 s microgravity each parabola Elliptic path relative to the centre of the Earth
18 Experiment Design 18 Experiment components: Elegant Breadboard Model Orbiting Sample (OS) OS Launcher Trap Safety brake Frame Structure Protective Layer Acquisition and Control System
19 Parabolic Flight Experiment Design: OS launcher 19 Fully manual OS launcher: Initial OS velocity, from 0.1 to 0.2 m/s; Easy 5 degree predefined attitude misalignment (included into attitude correction); Easy 10 cm predefined radial misalignment (included into initial offset correction; OS retention under an acceleration of 2g in all directions; Simple reset; Quick launch.
20 Parabolic Flight Test Objectives 20 Type of Test Test Article Test Objective Test facility Demonstrate of arm actuation functionalities in microgravity environment Demonstrate motor capability of withstanding OS impacts in capture configuration Demonstrate of OS detection in microgravity environment Parabolic Flight EBM Demonstrate of retention operation in microgravity environment Novespace Demonstrate transfer capability in microgravity environment Demonstrate funnel capability of withstanding OS impacts Raise TRL to 6
21 Parabolic Flight Test Plan 21 First Day The first set: verify the arm functioning (opening, closure and holding); The second set: verify retention maintaining with the OS inside funnel; The third set: verify the transfer operation; The fourth and fifth sets: verify OS launcher operations and OS trajectory; The sixth set: verify OS launch, sensor triggering and arm closure. Second and Third days Complete test execution. Set OS initial angle [deg] OS initial offset [cm]
22 Parabolic Flight Test Results 22 Test Day Test Case OS Initial Condition Speed Offset Angle Success [%] Success with triggered sensors [%] Success with OS inside funnel for more than 4s [%] [cm/s] [cm] [deg] INIT CAPT TRA LNC RET * (5/6) 100 (5/5) 100 (5/5) C (2/4) 100 (2/2) 100 (2/2) (4/4) 100 (4/4) 100 (4/4) (3/4) 100 (3/3) 100 (3/3) TOT (14/18) 100 (14/14) 100 (14/14) (8/10) 80 (8/10) 100 (8/8) C (2/4) 50 (2/4) 100 (2/2) (3/5) 75 (3/4) 100 (4/4) (7/9) 100 (7/7) 100 (7/7) TOT (20/28) 83 (20/24) 100 (20/20) Transfer completed within one parabola No pinching during transfer Launch affected by microgravity perturbations Successful execution of complete test within one parabola (~22 s) Failed test due to perturbations Occasional Arm/OS impacts before retention Retention successful even when the OS was manually delivered inside the funnel to react to perturbations
23 Parabolic Flight Test Results 23 DAY 2 Perturbations effects analysis Aircraft acceleration between OS launch and first impact with funnel Release time measured through the video analysis OS velocity: - acceleration measurements integrations - speed provided from launcher OS trajectory: - velocity integration. Successful test Failed test OS-funnel impact area
24 Parabolic Flight Test Results 24 DAY 2 Perturbations effects analysis OS-funnel edge impact at entering conditions Upward perturbation acceleration at launch (green vertical line)
25 Parabolic Flight Test Results 25 OS impacts Calculated from OS acceleration measurements OS-Funnel Forces higher than expected (design phase) cm/s Higher impact velocity Higher forces in Day 3 tests (higher OS speed) Impact duration as expected (design phase) ms No visible damage to protective layer Need for less stiff material or no protective layer at all OS-Arm Short Impact duration (~20 ms) Unknown impact distance from actuation chain Not directly comparable with maximum motor torque No motor synchronization loss recorded during impacts Force [N] Duration [ms] Day 2 Day 3 Day 2 Day 3 Mean Maximum Minimum Force [N] Day 2 Day 3 Mean Maximum Minimum
26 Parabolic Flight Test Results 26 Microgravity phase example OS-Funnel impacts OS-Arm impact
27 Parabolic Flight Test Results 27 Microgravity Perturbations Smooth parabola Low perturbations (first half) Successful test Disturbed parabola High perturbations: 0,05g peak Z acceleration; 0,02g mean Y acceleration during launch (first 5 seconds) Failed test
28 Conclusion 28 On-ground test campaign successfully completed Breadboard design effective both at system and component level in laboratory environment EBM able of withstanding mechanical and thermal loads induced during all mission phases Breadboard performances not affected from environmental loads TRL-4 achieved Parabolic flight test campaign successfully completed EBM full functionality in relevant 0-g environment Test cases doubled with respect to test plan Strong perturbations effect on OS during free floating phase resulting in some failed tests OS trajectory not rectilinear OS speed higher than requirements Testing condition more demanding with respect to design phase estimation Design concept robust and reliable Arm and funnel geometry Arm closure speed Detection sensors position Possible improvement: implementation of automatic release mechanism triggered by acceleration sensor TRL-6 achieved
29 Complete test example 29
30 ASTRA 2015, Noordwijk, The Netherlands, 11 May 2015 Thank you for the attention Questions?
31 ASTRA 2015, Noordwijk, The Netherlands, 11 May 2015 Backup
32 Parabolic Flight Test Results 32 DAY 1 Test ID Result Remarks 1 INIT 2 CAPT 3 - TRA 1 N/A Not available for tests 2 OK Only deployment 3 OK Only closure 4 OK Only deployment 5 OK Only closure 6 OK Only deployment 1 OK 2 OK 3 OK 4 OK 5 OK 1 OK First half of transfer 2 OK Transfer completion 3 OK 4 OK 5 OK Test ID Result Remarks 4 LNC 5 LNC 6 - RET 1 ENTER 2 ENTER 3 ENTER 4 ENTER 5 ENTER 1 ENTER 10cm offset 2 ENTER 10cm offset 3 ENTER 4 ENTER 5 ENTER 1 SUCCESS No arm/os impacts 2 SUCCESS Arm/OS impacts 3 FAIL 10cm offset 4 FAIL 10cm offset 5 SUCCESS 10cm offset Arm/OS impact No pinching during transfer OS Launch affected by microgravity perturbations
33 Parabolic Flight Test Results 33 DAY 2 attempting execution of complete test within one parabola Test ID Result Remarks 1 1 N/A Not available for tests INIT 2 OK RET 3 SUCCESS Arm/OS impacts TRA 4 OK RET 5 SUCCESS Arm/OS impacts TRA 6 OK 2 C-15 3 C-15 1 SUCCESS Arm/OS impacts 2 OK Transfer 3 FAIL 4 SUCCESS Arm/OS impacts 5 SUCCESS 1 FAIL 2 SUCCESS Switch to retention Arm/OS impacts 3 OK Transfer 4 SUCCESS Arm/OS Pinching 5 FAIL Test ID Result Remarks 4 C-15 5 C-15 1 SUCCESS 2 SUCCESS 3 SUCCESS 4 FAIL 5 SUCCESS 1 MISSED 2 SUCCESS Switch to retention 3 OK Transfer 4 SUCCESS Switch to retention Arm/OS impacts 5 SUCCESS Arm/OS impacts Successful execution of complete test within one parabola Failed test due to perturbations
34 Parabolic Flight Test Results 34 DAY 3 OS 20cm/s (not 10cm/s) because of perturbations Test ID Result Remarks 1 1 N/A Not available for tests INIT 2 SUCCESS C-20 3 FAIL C-20 4 SUCCESS C-20 5 SUCCESS C-20 6 SUCCESS Arm/OS impacts 2 C-20 3 C-20 1 SUCCESS 2 SUCCESS 3 SUCCESS 4 SUCCESS Arm/OS impacts 5 FAIL 1 SUCCESS 0 offset Arm/OS impacts 2 SUCCESS Arm/OS impacts 3 FAIL 4 SUCCESS Arm/OS impacts 5 FAIL Test ID Result Remarks 4 C-20 5 C-20 6 C-20 1 SUCCESS 2 FAIL 3 FAIL 4 SUCCESS 5 SUCCESS Arm/OS impacts 1 SUCCESS 2 FAIL 3 SUCCESS 4 FAIL 5 SUCCESS Arm/OS impacts 1 SUCCESS 2 SUCCESS 3 SUCCESS Arm/OS impacts 4 SUCCESS Arm/OS impacts 5 N/A N/A Failed test due to perturbations
35 Parabolic Flight Test Results 35 Retention test
36 Complete test example 36 Successful test
37 Complete test example 37 Failed test
38 Parabolic Flight Test Results 38 DAY 3 Perturbations effects analysis Aircraft acceleration between OS launch and first impact with funnel Release time measured through the video analysis OS velocity: - acceleration measurements integrations - speed provided from launcher OS trajectory: - velocity integration. Successful test Failed test OS-funnel impact area
39 Parabolic Flight Test Results 39 DAY 3 Perturbations effects analysis OS entered funnel close to nominal conditions Perturbation forced OS to escape funnel before arm reached retention configuration
40 Parabolic Flight Test Results 40 OS speed Number of frames between start and stop of OS support plate Speeds lower than mode value due to launcher components friction Video fps Piston stroke [cm] Measured speed [cm/s] Mode [cm/s] Expected speed [cm/s] Test Day Test Day Test Day
41 Vibration tests 41 Sine test Y-axis First resonance frequency amplification of arm tip response EBM rigid behaviour below 100HZ
42 Vibration tests 42 Random tests - 3σ rms response Location X [g] Y [g] Z [g] test FEM test FEM test FEM Arm tip Funnel top Arm shaft Lug top HDRM/arm Motor flange
EQUIPMENT INTERFACE LOAD CHARACTERIZATION IN ACOUSTICS
1 EQUIPMENT INTERFACE LOAD CHARACTERIZATION IN ACOUSTICS Nicolas Ludovic LARUE (1), Jean Marie LOME (2), Alice PRADINES (3) (1) Mechanical analysis and test engineer, EADS Astrium - 31 avenue des Cosmonautes,
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 informationCALIBRATION MECHANISM FOR INFRARED SPACE TELESCOPE. Patrice Kerhousse
CALIBRATION MECHANISM FOR INFRARED SPACE TELESCOPE Patrice Kerhousse Alcatel space industries Boulevard du Midi, BP 99-06156 Cannes la Bocca Cedex Telephone : 33-(0)4-92-92-72-38 / Fax : 33-(0)4-92-92--20
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 informationGAIA M2M POINTING MECHANISM QUALIFICATION
GAIA M2M POINTING MECHANISM QUALIFICATION Carlos Compostizo (1), Ricardo López (1), Laura Rivera (1) (1) SENER-Structures & Mechanisms Section, Av. Zugazarte 56, 4893 Las Arenas (Vizcaya) Spain Tel: 34944817578
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 informationFORCE LIMITED VIBRATION TESTING OF CASSINI SPACECRAFT COSMIC DUST ANALYSER
FORCE LIMITED VIBRATION TESTING OF CASSINI SPACECRAFT COSMIC DUST ANALYSER Heiko Jahn*, Swen Ritzmann*, Kurng Chang**, Terry Scharton** * German Aerospace Research Establishment, Institute for Space Sensor
More informationEUCLID M2 MIRROR MECHANISM
EUCLID M2 MIRROR MECHANISM Aiala Artiagoitia (1), Carlos Compostizo (1), Laura Rivera (1) (1) SENER, Av. Zugazarte 56, 48930 Las Arenas (Bizkaia) Spain, Email: aiala.artiagoitia@sener.es ABSTRACT Euclid
More informationSpacer Development and Analysis
Spacer Development and Analysis Mission Overview POPACS MISSION To measure changes in the density of the auroral zone upper atmosphere in response to various solar stimuli DREXEL OBJECTIVE To design and
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 informationFlight 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
More informationLUNAR ICY SOIL SAMPLING
LUNAR ICY SOIL SAMPLING Presenter: M. Savoia - Selex ES ASTRA 2015 11-13 May 2015, Noordwijk (NL) Table of contents Introduction Drill and Sampling Requirements Drill Preliminary Configuration Current
More informationSemi-Analytical Guidance Algorithm for Fast Retargeting Maneuvers Computation during Planetary Descent and Landing
ASTRA 2013 - ESA/ESTEC, Noordwijk, the Netherlands Semi-Analytical Guidance Algorithm for Fast Retargeting Maneuvers Computation during Planetary Descent and Landing Michèle LAVAGNA, Paolo LUNGHI Politecnico
More informationBINARY ASTEROID ORBIT MODIFICATION
2013 IAA PLANETARY DEFENSE CONFERENCE BEAST BINARY ASTEROID ORBIT MODIFICATION Property of GMV All rights reserved TABLE OF CONTENTS 1. Mission Concept 2. Asteroid Selection 3. Physical Principles 4. Space
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 informationLinear guide drives. Synchronous shafts The use of synchronous shafts enables several linear axes to be operated with one drive.
Linear guide drives Drive concept The linear guides are driven via the hollow shaft in the drive head. The drive head is used to directly install a motor or alternatively (in connection with a center shaft)
More informationCHAPTER 3 PERFORMANCE
PERFORMANCE 3.1 Introduction The LM-3A performance figures given in this chapter are based on the following assumptions: Launching from XSLC (Xichang Satellite Launch Center, Sichuan Province, China),
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 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 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 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 informationAsteroid 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
More informationVIBRATION ANALYSIS AND REPAIR PROCESS FOR THE VENTILATION SYSTEM FOR SMOKE DRAIN IN THE THERMAL POWER PLANT
Applied Engineering Letters Vol.3, No.1, 40-45 (2018) e-issn: 2466-4847 VIBRATION ANALYSIS AND REPAIR PROCESS FOR THE VENTILATION SYSTEM FOR SMOKE DRAIN IN THE THERMAL POWER PLANT Original scientific paper
More informationEvolution of an Integrated Actuation Mechanism for Planetary Exploration Using Dual-Reciprocating Drilling
Evolution of an Integrated Actuation Mechanism for Planetary Exploration Using Dual-Reciprocating Drilling By Craig Pitcher, Surrey Space Centre Prof. Yang Gao, Surrey Space Centre & Dr. Lutz Richter,
More informationDEOS AUTOMATION AND ROBOTICS PAYLOAD
w e. c r e a t e. s p a c e. Kayser-Threde GmbH Space Industrial Applications DEOS AUTOMATION AND ROBOTICS PAYLOAD 11th Symposium on Advanced Space Technologies in Robotics and Automation ESA/ESTEC, Noordwijk,
More informationHermes Experiment Opportunities
Hermes Experiment Opportunities Kristen John (PI) and Marc Fries Astromaterials Research and Exploration Science (ARES) NASA Johnson Space Center Houston, TX Strata-1 and Hermes Strata-1 is a Class 1E
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 informationCIRCULAR MOTION. Physics Department Electricity and Magnetism Laboratory. d dt. R is the distance from the body to the axis of rotation. v R.
Physics Department Electricity and Magnetism Laboratory CIRCULAR MOTION 1. Aim The aim of this experiment is to study uniform circular motion and uniformly accelerated circular motion. The motion equation
More informationPERFORMANCE EVALUATION OF OVERLOAD ABSORBING GEAR COUPLINGS
International Journal of Mechanical Engineering and Technology (IJMET) Volume 9, Issue 12, December 2018, pp. 1240 1255, Article ID: IJMET_09_12_126 Available online at http://www.ia aeme.com/ijmet/issues.asp?jtype=ijmet&vtype=
More informationUniversity of Bristol - Explore Bristol Research. Publisher's PDF, also known as Version of record
Noel, J. P., Renson, L., & Kerschen, G. (214). Experimental analysis of 2:1 modal interactions with noncommensurate linear frequencies in an aerospace structure. In ENOC 214 - Proceedings of 8th European
More informationarxiv:gr-qc/ v1 15 Nov 2004
Mission design for LISA Pathfinder arxiv:gr-qc/0411071v1 15 Nov 2004 M Landgraf, M Hechler, and S Kemble ESA/ESOC, Robert-Bosch-Straße 5, D-64293 Darmstadt, Germany E-mail: Markus.Landgraf@esa.int EADS
More informationDynamic Tests on Ring Shear Apparatus
, July 1-3, 2015, London, U.K. Dynamic Tests on Ring Shear Apparatus G. Di Massa Member IAENG, S. Pagano, M. Ramondini Abstract Ring shear apparatus are used to determine the ultimate shear strength of
More informationHigh Power Electric Propulsion Pointing Mechanisms (HP EPPM) Technical Development Activities (TDA s) strategy, status and planning
High Power Electric Propulsion Pointing Mechanisms (HP EPPM) Technical Development Activities (TDA s) strategy, status and planning Objectives of this presentation are: To provide primes with: ESA preliminary
More informationJonathan Fraser METEOR Project P07102 Environmental Test Stand Project Manager/Lead Engineer Detail Design Review Report
Jonathan Fraser METEOR Project P07102 Environmental Test Stand Project Manager/Lead Engineer Detail Design Review Report The project, P07102 Environmental Test Stand, is specifically involved in the design,
More informationPrecision Ball Screw/Spline
58-2E Models BNS-A, BNS, NS-A and NS Seal Outer ring Shim plate Seal Spline nut Seal Collar Shim plate Seal End cap Ball Outer ring Ball screw nut Outer ring Ball Retainer Retainer Outer ring Point of
More informationADCSS 2017: Sodern presentation
ADCSS 2017: Sodern presentation 1 Agenda Star trackers road map: a wide range of products End of CCD star trackers: SED26 replaced by Horus as standalone multi mission star tracker Hydra maintained beyond
More informationFormation Flying and Rendezvous and Docking Simulator for Exploration Missions (FAMOS-V2)
Formation Flying and Rendezvous and Docking Simulator for Exploration Missions (FAMOS-V2) Galder Bengoa, F. Alonso, D. García, M. Graziano (GMV S.A.) Dr. Guillermo Ortega (ESA/ESTEC) 2nd ESA Workshop on
More informationDevelopment 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
More informationRELATIVE MISSION ANALYSIS FOR PROBA 3: SAFE ORBITS AND CAM
5TH INTERNATIONAL CONFERENCE ON SPACECRAFT FORMATION FLYING MISSIONS AND TECHNOLOGIES RELATIVE MISSION ANALYSIS FOR PROBA 3: SAFE ORBITS AND CAM Munich, 31 st May 2013 T. V. Peters D. Escorial Presented
More informationTHE NEW 1.1 MN m TORQUE STANDARD MACHINE OF THE PTB BRAUNSCHWEIG/GERMANY
THE NEW 1.1 MN m TORQUE STANDARD MACHINE OF THE PTB BRAUNSCHWEIG/GERMANY D. Peschel 1, D. Mauersberger 1, D. Schwind 2, U. Kolwinski 2 1 Solid mechanics department, PTB, Germany 2 Gassmann Theiss Messtechnik
More informationThe AEOLUS Mission - In Orbit Commissioning and Verification
The AEOLUS Mission - In Orbit Commissioning and Verification ADM-Aeolus CAL/VAL Workshop, ESRIN P McGoldrick, J Brewster, J Marshall, F Fabre Airbus Defence and Space, UK and France 12 th February 2015
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 informationINVESTIGATION OF FRICTION HYSTERESIS USING A LABORATORY- SCALE TRIBOMETER
INVESTIGATION OF FRICTION HYSTERESIS USING A LABORATORY- SCALE TRIBOMETER P. D. Neis 1,2, P. De Baets 2, Y. Perez Delgado 2 and N. F. Ferreira 1 1 Federal University of Rio Grande do Sul, Brazil 2 Ghent
More informationDYNAMICS ME HOMEWORK PROBLEM SETS
DYNAMICS ME 34010 HOMEWORK PROBLEM SETS Mahmoud M. Safadi 1, M.B. Rubin 2 1 safadi@technion.ac.il, 2 mbrubin@technion.ac.il Faculty of Mechanical Engineering Technion Israel Institute of Technology Spring
More informationBUILDING LOW-COST NANO-SATELLITES: THE IMPORTANCE OF A PROPER ENVIRONMENTAL TESTS CAMPAIGN. Jose Sergio Almeida INPE (Brazil)
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
More informationMixing in Colliding, Ultrasonically Levitated Drops
Mixing in Colliding, Ultrasonically Levitated Drops Supporting information Details of acoustic levitation. Delivering drops into the acoustic levitation zone is easily ignored as a challenging first step
More informationEHD PUMP Conceptual Design Review University of Nebraska - Lincoln NASA Goddard Space Flight Center
EHD PUMP Conceptual Design Review University of Nebraska - Lincoln NASA Goddard Space Flight Center Mission Overview Experiment goals Theories of Operation Concept of Operation Experiment Application Past
More informationThe Archimedes Mars balloon project and the MIRIAM test flights Part 1: from Archimedes to MIRIAM
The Archimedes Mars balloon project and the MIRIAM test flights Part 1: from Archimedes to MIRIAM EMC13-13th European Mars Conference Kai Gehreth Jürgen Herholz Mars Society Deutschland www.marssociety.de
More informationELECTROMECHANICAL DESIGN OF A DRIVE MECHANISM FOR THE ROTATION OF THE SPECTROMETER WHEEL INSIDE MEDET EXPERIMENT
ELECTROMECHANICAL DESIGN OF A DRIVE MECHANISM FOR THE ROTATION OF THE SPECTROMETER WHEEL INSIDE MEDET EXPERIMENT A. Cozzani, B. Sarti, G. Casarosa, F. Ratti, M. Appolloni ESA-ESTEC Mechanical Testing Engineering
More informationLaunches and On-Orbit Performance
Launches and On-Orbit Performance An Update on Nanosatellite Missions at the UTIAS Space Flight Laboratory Daniel D. Kekez,, Robert E. Zee, Freddy M. Pranajaya Space Flight Laboratory University of Toronto
More informationAstrodynamics of Interplanetary Cubesats
Astrodynamics of Interplanetary Cubesats F. Topputo Politecnico di Milano, Italy 06 F. Topputo, Politecnico di Milano. All rights reserved. icubesat 06, 5th Interplanetary CubeSat Workshop 4-5 May 06,
More informationFin design mission. Team Members
Fin design mission Team Members Mission: Your team will determine the best fin design for a model rocket. You will compare highest altitude, flight characteristics, and weathercocking. You will report
More informationOUT-OF-PLANE MANOEUVRE CAMPAIGNS FOR METOP-A: PLANNING, MODELLING, CALIBRATION AND RECONSTRUCTION. +49(0) ,
OUT-OF-PLANE MANOEUVRE CAMPAIGNS FOR METOP-A: PLANNING, MODELLING, CALIBRATION AND RECONSTRUCTION Francisco Sancho (1), David Lázaro (2), Pier Luigi Righetti (3) (1) GMV at EUMETSAT, Eumetsat-Allee 1,
More informationSKF actuators available for quick delivery. Selection guide
SKF actuators available for quick delivery Selection guide A wide range of SKF actuators available for quick delivery Industrial actuator 24 Volt DC Load range 1 000 to 4 000 N Speed range 5 to 52 mm/s
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 informationAttitude control of a hopping robot: a feasibility study
Attitude control of a hopping robot: a feasibility study Tammepõld, R. and Kruusmaa, M. Tallinn University of Technology, Estonia Fiorini, P. University of Verona, Italy Summary Motivation Small mobile
More informationVane Type Rotary Actuators Series Variations
Vane Type Rotary Actuators Series Variations Vane Type Exterior CRB Series 0,, 0,, CRBU Series 0,, 0,, CRB Series, 6, 80, Has a compact body with exterior dimensions that do not change regardless of the
More informationVariable Capacitance Accelerometers: Design and Applications
Variable Capacitance Accelerometers: Design and Applications Micromachined silicon variable-capacitance accelerometers are designed for easy manufacture and demanding applications. Tom Connolly, Endevco
More informationScience in Microgravity ESAC
Science in Microgravity ESAC 15.12.2016 Science in Microgravity Microgravity (µg)! On the subject: what s that? Where Gravity is not felt Where Gravity is [almost] the only force Where weight of everything
More informationSelection Calculations For Linear & Rotary Actuators
H-8 For Electric Linear Slides and Electric Cylinders First determine your series, then select your product. Select the actuator that you will use based on the following flow charts: Selection Procedure
More informationTrajectory Planning, Setpoint Generation and Feedforward for Motion Systems
2 Trajectory Planning, Setpoint Generation and Feedforward for Motion Systems Paul Lambrechts Digital Motion Control (4K4), 23 Faculty of Mechanical Engineering, Control Systems Technology Group /42 2
More informationMounts for large lens in cooled environment
Mounts for large lens in cooled environment Thierry VIARD / Christophe DEVILLIERS Thales Alenia Space TAS Cannes La Bocca, France Thierry.viard@thalesaleniaspace.com Vincent COSTES / Didier GANGLOFF Centre
More informationLECTURE 12. STEADY-STATE RESPONSE DUE TO ROTATING IMBALANCE
LECTURE 12. STEADY-STATE RESPONSE DUE TO ROTATING IMBALANCE Figure 3.18 (a) Imbalanced motor with mass supported by a housing mass m, (b) Freebody diagram for, The product is called the imbalance vector.
More informationREDUCTION OF OVERTESTING DURING BASE-DRIVE RANDOM VIBRATION TESTS FOR THE EUCLID SPACECRAFT HARDWARE
COMPDYN 2013 4th ECCOMAS Thematic Conference on Computational Methods in Structural Dynamics and Earthquake Engineering M. Papadrakakis, V. Papadopoulos, V. Plevris (eds.) Kos Island, Greece, 12 14 June
More information7th ESA Workshop on Advanced Space Technologies for Robotics and Automation 'ASTRA 2002' ESTEC, Noordwijk, The Netherlands, November 19-21, 2002
µ'hh'ul GULOOWRROSURWRW\SHDQGGULOOLQJV\VWHP GHYHORSPHQWIRU0DUVVRLOVDPSOLQJDSSOLFDWLRQV (5H3*0DJQDQL7
More informationDynamics Kinetics of a particle Section 4: TJW Force-mass-acceleration: Example 1
Section 4: TJW Force-mass-acceleration: Example 1 The beam and attached hoisting mechanism have a combined mass of 1200 kg with center of mass at G. If the inertial acceleration a of a point P on the hoisting
More informationAdaptiveImpact Absorption. Smart Technology Centre
AdaptiveImpact Absorption Jan Holnicki-Szulc Institute of Fundamental Technological Research Smart Technology Centre http://smart.ippt.gov.pl Smart Technology Centre: 25 researchers (Smart Technologies
More informationScienceDirect. Response Spectrum Analysis of Printed Circuit Boards subjected to Shock Loads
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 144 (2016 ) 1469 1476 12th International Conference on Vibration Problems, ICOVP 2015 Response Spectrum Analysis of Printed
More informationAlta FT-150: The Thruster for LISA Pathfinder and LISA/NGO Missions
9 th LISA Symposium, Paris ASP Conference Series, Vol. 467 G. Auger, P. Binétruy and E. Plagnol, eds. c 2012 Astronomical Society of the Pacific Alta FT-150: The Thruster for LISA Pathfinder and LISA/NGO
More informationDEVELOPMENT OF INNOVATIVE MECHANICAL FLEXIBLE SOLAR ARRAY ARCHITECTURE
DEVELOPMENT OF INNOVATIVE MECHANICAL FLEXIBLE SOLAR ARRAY ARCHITECTURE Bernard BOULANGER (1), Yannick BAUDASSÉ (1), François GUINOT (1), Laurent D ABRIGEON (1), Mikaël THIBAUDEAU (1), Marina HEIM (2),
More informationBiological Experiments in Space
Veronica De Micco and Giovanna Aronne Biological Experiments in Space The experience of SAYSOY Space Apparatus to Yield SOYsprouts ARACNE Copyright MMVIII ARACNE editrice S.r.l. www.aracneeditrice.it info@aracneeditrice.it
More informationScience planning and operations for Mars Express
Science planning and operations for Mars Express René Pischel and Tanja Zegers ESA/ESTEC, Research and Scientific Support Department, Postbus 299, 2200 AG Noordwijk, The Netherlands I. Introduction The
More informationSP-1291 June Mars Express. The Scientific Investigations
SP-1291 June 2009 Mars Express The Scientific Investigations Operations and Archiving Mars Express Science Planning and Operations R. Pischel & T. Zegers ESA/ESTEC, Research and Scientific Support Department,
More informationSelection of Servomotors and Reducer Units for a 2 DoF PKM
Selection of Servomotors and Reducer Units for a 2 DoF PKM Hermes GIBERTI, Simone CINQUEMANI Mechanical Engineering Department, Politecnico di Milano, Campus Bovisa Sud, via La Masa 34, 20156, Milano,
More informationIdentification system for short product names. Changes/amendments at a glance. 2 Bosch Rexroth AG OBB omega modules R ( )
Omega Modules OBB 2 OBB omega modules R9990079 (206-05) Identification system for short product names Short product name Example: O B B - 085 - N N - System = Omega module Guideway = Ball Rail System Drive
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 informationVirtual Passive Controller for Robot Systems Using Joint Torque Sensors
NASA Technical Memorandum 110316 Virtual Passive Controller for Robot Systems Using Joint Torque Sensors Hal A. Aldridge and Jer-Nan Juang Langley Research Center, Hampton, Virginia January 1997 National
More informationAppendix A Satellite Mechanical Loads
Appendix A Satellite Mechanical Loads Mechanical loads can be static or dynamic. Static loads are constant or unchanging, and dynamic loads vary with time. Mechanical loads can also be external or self-contained.
More informationSelection Calculations For Motorized Actuators
Selection Calculations/ Selection Calculations For Linear Slides and Cylinders Select from the EZS Series, EZS Series for Cleanroom Use, EZC Series First determine your series, then select your model.
More informationTE 75R RESEARCH RUBBER FRICTION TEST MACHINE
TE 75R RESEARCH RUBBER FRICTION TEST MACHINE Background: The Research Rubber Friction Test Machine offers the ability to investigate fully the frictional behaviour of rubbery materials both in dry and
More informationSolid Propellant Autonomous DE-Orbit System [SPADES]
Solid Propellant Autonomous DE-Orbit System [SPADES] Solid Propellant Rocket Motor development Presented: Rogier Schonenborg Study: T. Soares J. Huesing A. Cotuna W. van Meerbeeck I. Carnelli L. Innocenti
More informationMars Sample Return Mission
Mars Sample Return Mission Ryan Supler Saylor.org: SSE101 MSRM Project April 15, 2014 2 Table of Contents The Scoping Elements of the Mars Sample Return Mission page 3 The High-Level Concept of Operations
More informationMars Sample Return (MSR) Mission BY: ABHISHEK KUMAR SINHA
Mars Sample Return (MSR) Mission BY: ABHISHEK KUMAR SINHA Samples returned to terrestrial laboratories by MSR Mission would be analyzed with state-of the-art instrumentation providing unprecedented insight
More informationHYPER Industrial Feasibility Study Final Presentation Optical Bench Activity 3, WP 3200
HYPER Industrial Feasibility Study Final Presentation Optical Bench Activity 3, WP 3200 ESTEC, Noordwijk The Netherlands 6 -th March 2003 Introduction 1 - Payload overall Architecture 2 - PST and OB design,
More informationJPL Flyby Mass Spectrometer
JPL Flyby Mass Spectrometer Kenneth Farley California Institute of Technology, Pasadena, CA 91125 Murray Darrach, Stojan Madzunkov, Rembrandt Schaefer, Evan Neidholdt Jet Propulsion Laboratory, California
More informationLecture «Robot Dynamics»: Dynamics 2
Lecture «Robot Dynamics»: Dynamics 2 151-0851-00 V lecture: CAB G11 Tuesday 10:15 12:00, every week exercise: HG E1.2 Wednesday 8:15 10:00, according to schedule (about every 2nd week) office hour: LEE
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 informationUSING ROTOR KIT BENTLY NEVADA FOR EXPERIMENTS WITH AEROSTATIC BEARINGS
USING ROTOR KIT BENTLY NEVADA FOR EXPERIMENTS WITH AEROSTATIC BEARINGS ŠIMEK, J. 1, KOZÁNEK, J., STEINBAUER, P., NEUSSER, Z. 3 1 TECHLAB Ltd., Prague, Institute of Thermomechanics AS CR 3 CTU in Prague,
More informationInverted Pendulum System
Introduction Inverted Pendulum System This lab experiment consists of two experimental procedures, each with sub parts. Experiment 1 is used to determine the system parameters needed to implement a controller.
More informationELEC4631 s Lecture 2: Dynamic Control Systems 7 March Overview of dynamic control systems
ELEC4631 s Lecture 2: Dynamic Control Systems 7 March 2011 Overview of dynamic control systems Goals of Controller design Autonomous dynamic systems Linear Multi-input multi-output (MIMO) systems Bat flight
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 informationMASS LOADING EFFECTS FOR HEAVY EQUIPMENT AND PAYLOADS Revision F
MASS LOADING EFFECTS FOR HEAVY EQUIPMENT AND PAYLOADS Revision F By Tom Irvine Email: tomirvine@aol.com May 19, 2011 Introduction Consider a launch vehicle with a payload. Intuitively, a realistic payload
More informationVibration Suppression of a 2-Mass Drive System with Multiple Feedbacks
International Journal of Scientific and Research Publications, Volume 5, Issue 11, November 2015 168 Vibration Suppression of a 2-Mass Drive System with Multiple Feedbacks L. Vidyaratan Meetei, Benjamin
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 informationSERVOMOTOR SIZING AND APPLICATION. Gary Kirckof, P.E.
SERVOMOTOR SIZING AND APPLICATION by Gary Kirckof, P.E. Basic Contents About the Author xvii Introduction xix 1 Kinematics 1 Introduction 1 Rectilinear Motion 2 Position and Distance 2 Velocity and Speed
More informationPerformance Investigation of an Experimental Shale Shaker in Filtration of. Saeid G.Benis George G.Chase Brad Jones Thomas Geehan
Performance Investigation of an Experimental Shale Shaker in Filtration of Water-Sand Slurry Saeid G.Benis George G.Chase Brad Jones Thomas Geehan Outline Goal Introduction Shale Shaker Particle Dynamics
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 informationOBSERVATIONS ON THE INFLUENCE OF LAUNCH VIBRATION ON BEARING TORQUE AND LUBRICANT PERFORMANCE
OBSERVATIONS ON THE INFLUENCE OF LAUNCH VIBRATION ON BEARING TORQUE AND LUBRICANT PERFORMANCE S.D. Lewis 1, S. Söchting 1, 2, E.W. Roberts 1, I. Sherrington 2 1 ESTL, AEA Technology Space, Birchwood Technology
More informationCHAPTER 10 TEST REVIEW
IB PHYSICS Name: Period: Date: # Marks: 69 Raw Score: IB Curve: DEVIL PHYSICS BADDEST CLASS ON CAMPUS CHAPTER 10 TEST REVIEW 1. A spacecraft travels away from Earth in a straight line with its motors shut
More informationMotors Automation Energy Transmission & Distribution Coatings. Servo Drive SCA06 V1.5X. Addendum to the Programming Manual SCA06 V1.
Motors Automation Energy Transmission & Distribution Coatings Servo Drive SCA06 V1.5X SCA06 V1.4X Series: SCA06 Language: English Document Number: 10003604017 / 01 Software Version: V1.5X Publication Date:
More information