Скачать презентацию QB 50 Project in response to FP 7 Скачать презентацию QB 50 Project in response to FP 7

467bd2b23f0f21a1f3f85eed8828b1c6.ppt

  • Количество слайдов: 29

QB 50 Project in response to FP 7 Space 2010 call “Facilitating access to QB 50 Project in response to FP 7 Space 2010 call “Facilitating access to space for small scale missions” J. Muylaert, C. O. Asma, R. Reinhard von Karman Institute for Fluid Dynamics Rhode-Saint-Genèse (Brussels) SEMWO 2011 November 16 -18, 2011 Vilnius, Lithuania 1 von Karman Institute for Fluid Dynamics www. QB 50. eu

QB 50 - THE IDEA • An international network of 50 double Cube. Sats QB 50 - THE IDEA • An international network of 50 double Cube. Sats for multi-point, in-situ, longduration measurements in the lower thermosphere and for re-entry research • A network of 50 double Cube. Sats sequentially deployed (1 Cube. Sat every orbit) • Initial altitude: 320 km (circular orbit, i=79°) • Downlink using the Global Educational Network for Satellite Operations (GENSO) 2 von Karman Institute for Fluid Dynamics www. QB 50. eu

QB 50 – Studying Lower Thermosphere A network of 50 Cube. Sats in the QB 50 – Studying Lower Thermosphere A network of 50 Cube. Sats in the lower thermosphere compared to networks in higher orbits has the following advantages: • The lifetime of a Cube. Sat in the envisaged low-Earth orbit will only be three months, i. e. much less than the 25 years stipulated by international requirements related to space debris • A low-Earth orbit allows high data rates because of the short communication distances involved • In their low-Earth orbits, the Cube. Sats will be below the Earth’s radiation belts, which is very important because Cube. Sats use low-cost Commercial-Off-The-Shelf (COTS) components • The residual atmosphere at these altitudes would help the Cube. Sats to scan lower altitudes without onboard propulsion and also to achieve a stable attitude • The orbit of the International Space Station (ISS) is usually maintained between 335 km (perigee) and 400 km (apogee). If a network of many Cube. Sats is launched into an orbit that is above that of the ISS there is a danger of collision with the ISS when the orbits of the Cube. Sats decay due to atmospheric drag. If the initial orbit of the Cube. Sats is below 330 km there is no danger of collision. On all other missions Cube. Sats are a secondary payload, on QB 50 the Cube. Sats are the primary payload. 3 von Karman Institute for Fluid Dynamics www. QB 50. eu

QB 50 - THE IDEA On a Double Cube. Sat (10 x 20 cm QB 50 - THE IDEA On a Double Cube. Sat (10 x 20 cm 3): Science Unit: Lower Thermosphere Measurements ISIS 2 U Sensors to be selected by a Working Group Standard sensors for all Cube. Sats Functional Unit: Power, CPU, Telecommunication Optional Technology or Science Package Universities are free to design the functional unit 4 von Karman Institute for Fluid Dynamics www. QB 50. eu

QB 50 – Cube. Sat Community 2 Australia 1 Russia 3 Austria 2 Greece QB 50 – Cube. Sat Community 2 Australia 1 Russia 3 Austria 2 Greece 1 Singapore 4 Belgium 1 Hungary 1 Slovakia 1 Brazil 1 India 2 South Korea 1 Czech Republic 1 Iran 1 Spain 3 Canada 2 Ireland 1 Sweden 1 Chile 2 Israel 1 Taiwan 8 China 2 Italy 2 Turkey 2 Denmark 1 Lithuania 4 United Kingdom 1 Estonia 1 Netherlands 8 USA 1 Ethiopia 1 Norway 1 Vietnam 1 Finland 5 Peru 81 Letters of Intent 3 France 5 7 Germany 1 Portugal von Karman Institute for Fluid Dynamics www. QB 50. eu

WORK BREAKDOWN – Tasks 1, 2, 3 Task 1 Task 2 Task 3 Management WORK BREAKDOWN – Tasks 1, 2, 3 Task 1 Task 2 Task 3 Management Mission Analysis Launcher VKI Project management VKI Mission Requirements VKI WG & AC Meetings ISIS Deployment Strategy VKI Workshops & Dissemination See separate slide Task 4 Science & I. O. D. See separate slide Task 5 Operations VKI Ground Stations & Comms BIRA Data Proc & Archiving C. VKI Orbital Dynamics VKI Europe, Middle East, Afr CSs SSC ADCS & GPS STANFORD North & South American CSs EPFL Mission Control NPU Asian CSs ASTRIUM Quality Assurance von Karman Institute for Fluid Dynamics 6

WORK BREAKDOWN – Task 3 Launcher VKI/SRC VKI Launcher Programmatics Payload Bay Programmatics ASTRIUM WORK BREAKDOWN – Task 3 Launcher VKI/SRC VKI Launcher Programmatics Payload Bay Programmatics ASTRIUM QA, PA ISIS Deployment System Design SRC ISIS SHTIL 2. 1 Launcher and Operations M. A. I. T. ISIS Launcher Interface ISIS Launch campaign von Karman Institute for Fluid Dynamics 7

WORK BREAKDOWN – Task 4 Science & I. O. D. VKI Atmospheric Science In WORK BREAKDOWN – Task 4 Science & I. O. D. VKI Atmospheric Science In Orbit Technology Demonstration SSC System Engineering Inflate. Sail MSSL VKI Sensor selection and procurement Atmospheric Re. Entry VKI Formation Flight IAP DLR Measurement techniques von Karman Institute for Fluid Dynamics TU-DELFT Atmospheric Models Gossamer Solar. Sail Demonstration 8

Advisory Structure 9 von Karman Institute for Fluid Dynamics www. QB 50. eu Advisory Structure 9 von Karman Institute for Fluid Dynamics www. QB 50. eu

Sensor Selection Working Group Sensors reviewed: • • • Accelerometer Energetic Particle Sensors FIPEX Sensor Selection Working Group Sensors reviewed: • • • Accelerometer Energetic Particle Sensors FIPEX (oxygen sensor) GPS Ion Mass Spectrometer Langmuir Probe Laser Reflector Magnetometer Neutral Mass Spectrometer Spherical EUV and Plasma Spectrometer (SEPS) • Thermal Sensors (Incl. Bolometric Oscillation Sensor) • Wind Ion Neutral Composition Suite (WINCS - Armada) 10 von Karman Institute for Fluid Dynamics Information gathered for each sensor: • • • Science case Description Performance Mass Power Data rate Operations and Commanding Special requirements Heritage (TRL) Cost (development and per unit) • Development schedule www. QB 50. eu

Sensor Selection Working Group Cube. Sat Configuration • Spacecraft resources preclude accommodating all sensors Sensor Selection Working Group Cube. Sat Configuration • Spacecraft resources preclude accommodating all sensors on all Cube. Sats • Present sensor budget need to be increased for a scientifically compelling payload • Minimum baseline would be: – 10 x FIPEX+T+LR; 10 x NMS+T+LR; 10 x LP+T+LR; 10 x IMS+T+LR • Proposed baseline would be: – 20 x [FIPEX, NMS, Thermal, Laser Reflector] – 20 x [Langmuir Probe, IMS, Thermal, Laser Reflector] 11 von Karman Institute for Fluid Dynamics www. QB 50. eu

QB 50 – Orbital Dynamics To be determined: • Initial orbital altitude to ensure QB 50 – Orbital Dynamics To be determined: • Initial orbital altitude to ensure minimum lifetime of 3 months • Separation speed (present assumption in the range 1 to 5 m/s) • Should the Cube. Sats be deployed in flight direction, anti-flight direction, upward, downward, east or west direction? • Deployment sequence (1 Cube. Sat per orbit or 1 Cube. Sat every 2 or 3 orbits? ) • Which atmospheric models should be used (present assumption several different models) • Which trajectory simulation software should be used? • Which drag coefficient should be used (probably a range of coefficients) These questions will be addressed by the Orbital Dynamics Working Group (ODWG) 12 von Karman Institute for Fluid Dynamics www. QB 50. eu

Importance of Attitude Stability 13 von Karman Institute for Fluid Dynamics www. QB 50. Importance of Attitude Stability 13 von Karman Institute for Fluid Dynamics www. QB 50. eu

Lifetime Prediction (h 0 = 320 km) Launch 14 von Karman Institute for Fluid Lifetime Prediction (h 0 = 320 km) Launch 14 von Karman Institute for Fluid Dynamics www. QB 50. eu

Launch Vehicle • The Shtil -1 was used to launch : 15 • On Launch Vehicle • The Shtil -1 was used to launch : 15 • On the Shtil-1, the payload is placed inside a special container which is custom designed and mounted next to the third stage engine nozzle. • The Shtil-2. 1 is an improved version of the Shtil-1 where the payload is accommodated inside a fairing on top of the third stage • The Shtil-2. 1 is fully developed and hardware has been built and tested von Karman Institute for Fluid Dynamics Shtil-1 Shtil-2. 1 – TUBSAT-N (8 kg) and TUBSAT-N 1(3 kg) nanosatellites into a 400 x 776 km orbit on 7 July 1998 – Kompass-2 satellite (77 kg) into a 402 x 525 km orbit on 26 May 2006 www. QB 50. eu 15

QB 50 – Launching & Deployment 16 von Karman Institute for Fluid Dynamics www. QB 50 – Launching & Deployment 16 von Karman Institute for Fluid Dynamics www. QB 50. eu

QB 50 – Launching & Deployment Shtil - 2. 1 17 von Karman Institute QB 50 – Launching & Deployment Shtil - 2. 1 17 von Karman Institute for Fluid Dynamics www. QB 50. eu

QB 50 – Launching & Deployment QB 50 2014 18 Precursor flight 2013 von QB 50 – Launching & Deployment QB 50 2014 18 Precursor flight 2013 von Karman Institute for Fluid Dynamics Shtil - 2. 1 www. QB 50. eu

Study of platforms and deployers for Cube. Sats on SHTIL Cub. Sat containers Launcher Study of platforms and deployers for Cube. Sats on SHTIL Cub. Sat containers Launcher telemetry Optional : Solar Sail protective capsule 19 von Karman Institute for Fluid Dynamics SHTIL www. QB 50. eu

Accommodation on Shtil 2. 1 20 von Karman Institute for Fluid Dynamics (may not Accommodation on Shtil 2. 1 20 von Karman Institute for Fluid Dynamics (may not be to scale) www. QB 50. eu 20

QB 50 – Cube. Sat Accommodation Batt Lower bay and 3 rd stage engine QB 50 – Cube. Sat Accommodation Batt Lower bay and 3 rd stage engine 21 von Karman Institute for Fluid Dynamics Shtil - 2. 1 www. QB 50. eu

In-Orbit Technology Demonstration VKI’s Re-Entry Cube. Sat A modular deployment system for double and In-Orbit Technology Demonstration VKI’s Re-Entry Cube. Sat A modular deployment system for double and triple Cube. Sats Gossamer-1 Solar Sail demonstration package De-orbiting and debris mitigation by electrodynamic tether Other In-Orbit Demos: Inflate. Sail demonstration mission - End of life analysis, Debris - Formation flight - Micro-propulsion systems - Micro-g experiment 22 von Karman Institute for Fluid Dynamics www. QB 50. eu

Inflate-Sail for testing a solar sail with inflatable booms 23 von Karman Institute for Inflate-Sail for testing a solar sail with inflatable booms 23 von Karman Institute for Fluid Dynamics www. QB 50. eu

Gossamer-1 Project Solar Sail Deployment Demonstration • During the launch, the sail is stowed Gossamer-1 Project Solar Sail Deployment Demonstration • During the launch, the sail is stowed in a container (45 x 40 cm 3, 15 kg). • It remains attached to the third stage (to the deployment system) and uses the battery on board. • The solar sail is deployed after all the Cube. Sats • It brings down the Shtil 2. 1 3 rd stage in 15 days, thereby demonstrating rapid de-orbiting Solar sail attached to 3 rd stage sail and boom compartment 24 von Karman Institute for Fluid Dynamics www. QB 50. eu

VKI Re-Ent. Sat – Concept Atmospheric Re-Entry Flight Data Flight data for Debris/Disintegration Tool VKI Re-Ent. Sat – Concept Atmospheric Re-Entry Flight Data Flight data for Debris/Disintegration Tool (RAMSES) Validation Re-Ent. Sat to survive until ~70 km altitude • Light ablative material as thermal shield • Temperature & Pressure measurements on thermal shield • Skin friction measurements on the side 25 von Karman Institute for Fluid Dynamics Temperature field and heat flux estimations De-orbiting techniques using aerodynamic means www. QB 50. eu

Formation Flying Cube. Sats Del. FFI Project: with triple Cube. Sats “Delta” and “Phi” Formation Flying Cube. Sats Del. FFI Project: with triple Cube. Sats “Delta” and “Phi” • Delft University of Technology intends to provide two triple-unit Cubesats, both being equipped with a highly miniaturized propulsion system in addition to the standard science payload. • This allows for a coordinated formation flying of these two satellites using baselines, which can be realized, maintained and adjusted during the mission based on scientific and technological needs. • The position of the satellite will be determined by GPS. The inter-satellite communication will be realized by ground stations • Therefore, formation flight will be possible at any distance 26 von Karman Institute for Fluid Dynamics www. QB 50. eu

Call for Cube. Sat Proposals • The Call for Proposals will be issued on Call for Cube. Sat Proposals • The Call for Proposals will be issued on the QB 50 web site on 1 December 2011 • Deadline for submission of proposals to VKI 15 January 2011 • Proposal evaluation and clarification period 15 Jan – 20 Feb 2012 • Page limit: 15 pages - incl. figures, tables, references - excl. cover page, Table of Contents • Annexes for - Cost section (detailed and realistic cost breakdown - Cube. Sat management (organigramme, key personnel) • Availability of a ground station is an advantage but not a necessary condition for selection 27 von Karman Institute for Fluid Dynamics www. QB 50. eu

QB 50 NEWSLETTER • The QB 50 Newsletter No. 2 (mid September) will have QB 50 NEWSLETTER • The QB 50 Newsletter No. 2 (mid September) will have articles on - Status of the QB 50 project - Second QB 50 Workshop - 4 th European Cube. Sat Symposium - Call for Cube. Sat Proposals for QB 50 - Sensor selection - Ground station network - Frequency allocation - Deployment system - Gossamer-1 - A few articles on special double and triple Cube. Sats on QB 50 for science and technology demonstration If you wish to publish a short article (5 -20 lines) in the QB 50 Newsletter contact the Editor Cem O. Asma, [email protected] ac. be also if you wish to subscribe or unsubscribe to the Newsletter 28 von Karman Institute for Fluid Dynamics FP 7 QB 50 www. QB 50. eu

Important Dates: 30 Oct 2011: Deadline for the submission of abstracts CUBESAT SYMPOSIUM www. Important Dates: 30 Oct 2011: Deadline for the submission of abstracts CUBESAT SYMPOSIUM www. vki. ac. be/Cube. Sat. Symposium 15 Nov 2011: Notification of acceptance 15 Dec 2011: Publication of the programme and the abstracts 15 Jan 2012: Deadline for online registration 30 Jan-1 Feb 2012: Cube. Sat Symposium Registration fee: 100 € (this includes 3 lunches and all coffee breaks) 29 von Karman Institute for Fluid Dynamics www. QB 50. eu