QB50 Project in response to

von Karman Institute for Fluid Dynamics1 www.QB50.eu

J. Muylaert, C. O. Asma, R. Reinhard

von Karman Institute for Fluid DynamicsRhode-Saint-Genèse (Brussels)

SEMWO 2011 November 16-18, 2011

Vilnius, Lithuania

QB50 Project in response to

FP7 Space 2010 call “Facilitating access to space for small scale missions”


QB50 - THE IDEA

• An international network of 50 double CubeSats for multi-point, in-situ, long-duration measurements in the lower thermosphere and for re-entry research

• A network of 50 double CubeSats sequentially deployed (1 CubeSat every orbit)

• Initial altitude: 320 km (circular orbit, i=79°)

• Downlink using the Global Educational Network for Satellite Operations (GENSO)


QB50 – Studying Lower ThermosphereA network of 50 CubeSats in the lower thermosphere compared to networks in higher orbits has the following advantages:

• The lifetime of a CubeSat 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 CubeSats will be below the Earth’s radiation belts, which is very important because CubeSats use low-cost Commercial-Off-The-Shelf (COTS) components

• The residual atmosphere at these altitudes would help the CubeSats 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 CubeSats 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 CubeSats decay due to atmospheric drag. If the initial orbit of the CubeSats is below 330 km there is no danger of collision.

On all other missions CubeSats are a secondary payload, on QB50 the CubeSats are the primary payload.


QB50 - THE IDEA

Science Unit:

Lower Thermosphere Measurements

Sensors to be selected by a Working Group

Standard sensors for all CubeSats

Functional Unit:

Power, CPU, Telecommunication

Optional Technology or Science Package

Universities are free to design the functional unit

ISIS 2U

On a Double CubeSat (10 x 10 x 20 cm3):


QB50 – CubeSat Community7 Germany

2 Greece

1 Hungary

1 India

1 Iran

2 Ireland

2 Israel

2 Italy

1 Lithuania

1 Netherlands

1 Norway

5 Peru

1 Portugal

2 Australia

3 Austria

4 Belgium

1 Brazil

1 Czech Republic

3 Canada

1 Chile

8 China

2 Denmark

1 Estonia

1 Ethiopia

1 Finland

3 France

1 Russia

1 Singapore

1 Slovakia

2 South Korea

1 Spain

1 Sweden

1 Taiwan

2 Turkey

4 United Kingdom

8 USA

1 Vietnam

81 Letters of Intent

von Karman Institute for Fluid Dynamics 6

WORK BREAKDOWN – Tasks 1, 2, 3

See separate

slide

See separate

slide


WORK BREAKDOWN – Task 3


WORK BREAKDOWN – Task 4


Advisory Structure


Sensor Selection Working GroupSensors reviewed:

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

• 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)


Sensor Selection Working GroupCubeSat Configuration

• Spacecraft resources preclude accommodating all sensors on all CubeSats

• 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]


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 CubeSats be deployed in flight direction, anti-flight direction, upward,

downward, east or west direction?

• Deployment sequence (1 CubeSat per orbit or 1 CubeSat 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)

QB50 – Orbital Dynamics


Importance of Attitude Stability


Lifetime Prediction (h0 = 320 km)

Launch

von Karman Institute for Fluid Dynamics15 www.QB50.eu 15

• The Shtil -1 was used to launch : – TUBSAT-N (8kg) and TUBSAT-N1(3kg) nanosatellites

into a 400x776 km orbit on 7 July 1998

– Kompass-2 satellite (77kg) into a 402x525km orbit on 26 May 2006

• 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

Launch VehicleS

hti

l-2.

1

Sh

til-

1


QB50 – Launching & Deployment



Shtil - 2.1



Shtil - 2.1

QB502014

Precursor flight2013


Study of platforms and deployers for CubeSats on SHTIL

SHTIL

CubSat containers

Optional :Solar Sail protective capsule

Launcher telemetry


Accommodation on Shtil 2.1

20

(may not be to scale)


QB50 – CubeSat Accommodation

Shtil - 2.1

Lower bay and 3rd stage engine

Batt


A modular deployment system for double and triple CubeSats

Gossamer-1 Solar Sail demonstration package

InflateSail demonstration mission

Other In-Orbit Demos:

- End of life analysis, Debris

- Formation flight

- Micro-propulsion systems

- Micro-g experiment

In-Orbit Technology Demonstration

De-orbiting and debris mitigation by electrodynamic tether

VKI’s Re-Entry CubeSat


Inflate-Sail for testing a solar sail with inflatable booms


Gossamer-1 ProjectSolar Sail Deployment Demonstration

sail and boom compartment

Solar sail attached to 3rd stage

• During the launch, the sail is stowed in a container (45 x 45 x 40 cm3

, 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 CubeSats

•It brings down the Shtil 2.1 3rd stage in 15 days, thereby demonstrating rapid de-orbiting


VKI Re-EntSat – Concept

•Light ablative material as thermal shield

•Temperature & Pressure measurements on the thermal shield

•Skin friction measurements on the side

Atmospheric Re-Entry Flight Data

Flight data for Debris/Disintegration Tool (RAMSES) Validation

Re-EntSat to survive until ~70 km altitude

De-orbiting techniques using aerodynamic means

Temperature field and heat flux estimations


Formation Flying CubeSatsDelFFI Project: with triple CubeSats “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


Call for CubeSat Proposals• The Call for Proposals will be issued on the QB50 web site on

1 December 2011

• Deadline for submission of proposals to VKI15 January 2011

• Proposal evaluation and clarification period15 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- CubeSat management (organigramme, key personnel)

• Availability of a ground station is an advantage but not a necessary condition for selection


QB50 NEWSLETTER• The QB50 Newsletter No.2 (mid September) will have articles on

- Status of the QB50 project

- Second QB50 Workshop

- 4th European CubeSat Symposium

- Call for CubeSat Proposals for QB50

- Sensor selection

- Ground station network

- Frequency allocation

- Deployment system

- Gossamer-1

- A few articles on special double and triple CubeSats on QB50 for science and technology demonstration

If you wish to publish a short article (5-20 lines) in the QB50 Newsletter contact the Editor

Cem O. Asma, [email protected]

also if you wish to subscribe or unsubscribe to the Newsletter

FP7QB50


Important Dates:

30 Oct 2011:Deadline for the submission of abstracts

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: CubeSat Symposium

Registration fee: 100 €

(this includes 3 lunches and all coffee breaks)

www.vki.ac.be/CubeSatSymposiumwww.vki.ac.be/CubeSatSymposium

CUBESAT SYMPOSIUM

QB50 Project in response to

Documents