ESA UNCLASSIFIED – Releasable to the Public Session 7: Science and engineering lessons from the de- orbiting and re-entry phase C. Pardini (1), H. Krag.

Slides:



Advertisements
Similar presentations
SWWT plenary meeting / 28 June 2011 Brussels Atmospheric Effects Topical Group Reporting period: 2010 – June ATMOP 2.MURI/NADIR (USA) 3.ESA GOCE+
Advertisements

Introduction to Astrophysics
Geospace Electrodynamic Connections (GEC) Mission The GEC mission has been in the formulation phase as part of NASA’s Solar Terrestrial Probe program for.
DEBRIS REMOVAL DESIGN DRIVERS BASED ON TARGET SELECTION 2 nd European Workshop on Active Debris Removal CNES HQ, Paris, 18 th - 19 th July 2012 Adam White:
6. Space research and exploration of space increases our understanding of the Earth‘s own environment, the Solar System and the Universe. 4. Rapid advances.
M. R. Tetlow and C.J. Doolan School on Mechanical Engineering
THE AUSTRALIAN NATIONAL UNIVERSITY Infrasound Technology Workshop, November 2007, Tokyo, Japan OPTIMUM ARRAY DESIGN FOR THE DETECTION OF DISTANT.
National Aeronautics and Space Administration Orbital Debris Mitigation R. L. Kelley 1, D. R. Jarkey 2, G. Stansbery 3 1. Jacobs, NASA Johnson Space Center,
Formation Flying - T.Sugano Orbital Decay Perturbation in LEO is mainly due to atmospheric drag Orbital decay of space probes (e.g. Space Shuttle, ISS,
Federal Aviation Administration On-Orbit Debris Mitigation Methods for Upper Stages COMSTAC: Space Transportation Operations Working Group and Risk Management.
Principles of Propulsion and its Application in Space Launchers Prof. Dr.-Ing. Uwe Apel Hochschule Bremen REVA Seminar1.
The Lander is at a 25 km Lunar altitude and an orbital period of approximately 110 minutes. After separation occurs the Lander is completely self sufficient.
| Astronautics Research Group, Faculty of Engineering and the Environment University of Southampton,
The Four Candidate Earth Explorer Core Missions Consultative Workshop October 1999, Granada, Spain, Revised by CCT GOCE S 43 Science and.
FIREBIRD Ian Lyon Engineering and Physics Carroll College Simulation of the Precise Separation of a Two-Nanosatellite System using Differential Drag.
The Four Candidate Earth Explorer Core Missions Consultative Workshop October 1999, Granada, Spain, Revised by CCT GOCE S 59 Performance.
Preliminary Rocket Design Objectives: 1. Comprehend a preliminary sizing example for a rocket 2. Explain basic trade-offs in rocket design.
METEOR BACKGROUND This is a foundation project in an ambitious endeavor to provide the RIT research community with a means to conduct near space.
CISM Advisory Council Meeting 4 March Ionosphere-Thermosphere Modeling Tim Killeen, Stan Solomon, and the CISM Ionosphere-Thermosphere Team.
The impact of long-term trends on the space debris population Dr Hugh Lewis Astronautics Research Group, Faculty of Engineering & the Environment.
Presented at the Colorado Undergraduate Space Research Symposium April 20, 2013 Aurora, CO Team Charlie: Aaron Bartelt Stacie Noetzelmann Philip Jurney.
Long-term evolution of the space debris population Dr Hugh Lewis Astronautics Research Group, Faculty of Engineering & the Environment.
1 Samara State Aerospace University (SSAU) Modern methods of analysis of the dynamics and motion control of space tether systems Practical lessons Yuryi.
Sanitation Requirements in Space: The issues of Space Debris and its Management V. Adimurthy Indian Space Research Organisation.
An Assessment of CubeSat Collision Risk H.G. Lewis 1, B.S. Schwarz 1, S.G. George 1 and H. Stokes 2 1 Astronautics Research Group, Faculty of Engineering.
1 Section 03: Global Weather. 2 Lesson: 01 Professional Forecasting and Technology Section 4.9 Pages
Cubesats A spacecraft concept to provide advances in international cooperation From: Doug Rowland, NASA GSFC Alexi Glover, ESA.
The Effectiveness of Space Debris Mitigation Measures ISU’s 16 th Annual International Symposium 21 st February 2012 Adam E. White, Hugh G. Lewis, Hedley.
1 ORBITAL DEBRIS: TOWARDS SUSTAINABLE SPACE ACTIVITIES PARIS SPACE WEEK 2015 Christophe BONNAL CNES – Launcher Directorate – Senior Expert Chairman – Space.
AIAA RM Second ATS at UCCS Polar-Orbiting, Passive, Atmospheric Calibration Spheres (POPACS) Presented by R. Gilbert Moore Director, Project.
D rag and A tmospheric N eutral D ensity E xplorer (DANDE) Colorado Space Grant Consortium and CU Aerospace Engineering Sciences COSGC Symposium April.
The effect of modelling assumptions on predictions of the space debris environment R. Blake and H.G. Lewis Astronautics Research Group, Faculty of Engineering.
Lesson 3: Design for Remote Sensing Your Mission 1; just like a real CubeSat.
AAE 450- Propulsion LV Stephen Hanna Critical Design Review 02/27/01.
Space Science MO&DA Programs - September Page 1 SS It is known that the aurora is created by intense electron beams which impact the upper atmosphere.
Space Weather Modelling: from Science to Applications Chair: M. Dinguirard ONERA.
Modelling and Open Loop Simulation of Reentry Trajectory for RLV Missions Ashok Joshi and K. Sivan Department of Aerospace Engineering Indian Institute.
Coming Home. De-orbit burn The craft spins itself 180 degrees so that it is facing backward with respect to its velocity The engine is fired, decelerating.
Slide 1 Satellite Drag Modeling using Direct Simulation Monte Carlo (DSMC) Piyush M. Mehta and Craig A. McLaughlin The University of Kansas Acknowledgement:
1 MAVEN PFP ICDR May 23-25, 2011 Mars Atmosphere and Volatile EvolutioN (MAVEN) Mission Particles and Fields Science Critical Design Review May ,
Topics in Space Weather Earth Atmosphere & Ionosphere
CEOS Plenary Session Montreal, 4 November 2013 Stephen Briggs, ESA Head, Programme Planning and Coordination Service ESA’s Earth Observation Programme.
A&AE 450 – Senior Design Jeremy Davis Group A – Aerodynamics Preliminary Design Analysis January 23, 2001.
Dept. of Astronmy Optical surveys for space debris Byeon Jae Gyu.
National Aeronautics and Space Administration Space Debris Assessment for USA-193 Presentation to the 45 th Session of the Scientific and Technical Subcommittee.
AAE 450 – Spacecraft Design 1 Attitude Determination Methods Brienne Bogenberger January 18, 2004 Dynamics & Control Group Lead, Attitude Determination.
Capabilities of the to deal with space debris Capabilities of the Space Situation Monitoring and Analysis System (SSMAS) to deal with space debris.
ESA UNCLASSIFIED – Releasable to the Public Calibration of Radar Based Re-entry Predictions S. Lemmens (1), B. Bastida Virgili (1), T. Flohrer (1), H.
Thermospheric density variations due to space weather Tiera Laitinen, Juho Iipponen, Ilja Honkonen, Max van de Kamp, Ari Viljanen, Pekka Janhunen Finnish.
ESA UNCLASSIFIED – Releasable to the Public GOCE re-entry campaign B. Bastida Virgili, T. Flohrer, S. Lemmens, H. Krag ESA Space Debris Office, HSO-GR,
DAVINCI: Deep Atmosphere Venus Investigation of Noble Gas, Chemistry, and Imaging One out five NASA’s Discovery-class missions for Phase A studies. A 63.
CARPE DIEM Meeting Barcelona June 2002 RAINCLOUDS Satellite rain and cloud probing for monitoring and forecasting water resources at a range of time.
When Lower Atmosphere Waves Invade the Upper Atmosphere
The Legal Implications of Improved Space Situation Awareness and other Developments in Space Technology Dr Stuart Eves, SSTL.
Aerodynamic Attitude Control for CubeSats
Atmospheric Effects splinter – wrap up
SPACE DEBRIS Roger Thompson Sr. Engineering Specialist
Space Weather Activities in China
Space Junk Aerospace Engineering © 2011 Project Lead The Way, Inc.
Space Junk Aerospace Engineering © 2011 Project Lead The Way, Inc.
NASA Nasa's Parker Solar Probe mission set off to explore the Sun's atmosphere in the summer of The probe will swoop to within 4 million miles of.
Systems Engineering Management
Summary & recommendations multi-mission synergies session 9
Gamma Ray Observatory Potential attitude control problems may force NASA to deorbit one of its largest orbiting observatories as early as March. Launched.
Atmospheric Re-Entry Goal: To re-enter the CubeSat into the atmosphere and survive re-entry and hit the ground without any deceleration from parachute,
Rocketry Trajectory Basics
ATMOSPHERE ONLINE LAB.
CHEOPS - CHaracterizing ExOPlanet Satellite
The Deorbiting of GOCE – A Spacecraft Operations Perspective
Flight Operations for GOCE, ESA’s Gravity Mission
Presentation transcript:

ESA UNCLASSIFIED – Releasable to the Public Session 7: Science and engineering lessons from the de- orbiting and re-entry phase C. Pardini (1), H. Krag (2) (2) Institute of Information Science and Technologies, National Research Council of Italy (2) European Space Agency, Space Debris Office

ESA UNCLASSIFIED – Releasable to the Public GOCE and Re-entry Science Ca 70% the atmospheric re-entries occur in an uncontrolled way – Roughly 100 tons per year – 20-40% of the mass of larger structures typically survives Prediction accuracy of re-entry epoch and location is poor – Rule of thumb: prediction accuracy ≈ ± 20% of remaining prediction time Future missions will have to respect limits for the on-ground risk – Very constraining requirement with potentially large system impacts – Validation by simulation (confidence in the simulation needs to be high) After the loss of drag-free mode, GOCE became a reference object for (quasi) uncontrolled re-entries

ESA UNCLASSIFIED – Releasable to the Public Predicting Uncontrolled Re-entries Atmosphere model ( km) Solar and geomagnetic activity forecasts Attitude motion evolution (and motion measurements) Drag coefficient Quality of orbit determination results using radar ranging Effect of sparse ranging data GPS and ILRS reference Attitude data Drag levels ! GOCE data

ESA UNCLASSIFIED – Releasable to the Public Understanding Atmospheric Break-Up Altitude Aerodynamically induced torques dominate Peak Heating Peak deceleration Initial Heating ≈ 200km ≈ 120km ≈ 80-45km GPS and ILRS reference Attitude torques Drag levels Payload temperature sensors ! GOCE data Initial fragmentation ≈ 95km

ESA UNCLASSIFIED – Releasable to the Public Seed Questions To which degree will an upgraded atmospheric density models between 100km and 200km improve the prediction results? What can we learn in the area of ground-based measurements of uncooperative low altitude targets? What can we learn in terms of understanding how accurate our predictions are? What can we expect to learn from recorded component temperatures? To which degree are the results obtained with GOCE transferable to other uncontrolled re-entries? – Similarity to re-entering upper stages? Which kind of future data might be of interest for a further refinement of re-entry predictions?