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wp4 – CAPANINA Trial 2Neuchatel 27/10/05

Marco Bobbio Pallavicini (CGS)

Myles Capstik (UNY)

Joachim Horwath (DLR)

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Summary

Introduction to Trial 2

Comments on High Altitude Systems: constraints, mission planning, aerial segment design

High Altitude System : Preparation activities

RF experiment : Testbed description

RF experiment : Preparation activities

FSO experiment : Testbed description

FSO experiment : Preparation activities

Countdown and Launch ( 3 min FILM )

Comments on the flight mission

RF experiment : Operation and results

FSO experiment : Operation and results

Comments

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Capanina Network Concept

Up to 120Mbit/ssymmetric links

Fixed BFWA particularly for rural locations

WLAN

Moving TrainUp to 300km/h

Steerable/Smart Antenna

31/28GHz, (<11GHz),+ optical backhaul and interplatform

17-22km

To be validated:

RF link: stratospheric node - ground node

FSO link: stratospheric node - ground node

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CAPANINA Test Campaign

Broadband communications from the Stratosphere•Ka- band RF communication to ground users; fixed and mobiles (trains)

•Free Space Optics (laser) communication aimed to inter-platform links at high altitude

Trial 2 : High altitude test, by means of

Stratospheric BalloonSummer 2005, Kiruna, S

Trial 1 : Low altitude test, by means of Tethered

BalloonSummer 2004, Pershore, UK

Demonstration of a reduced network with FSO communication

within two flying platforms

2007 TBDTBD

Trial 3 : High altitude test, by means of Stratospheric

AirplaneSummer 2006, Kawai/Edwards

TBCTBC

Marco Bobbio Pallavicini – responsible test campaign & testbed system Marco Bobbio Pallavicini – responsible test campaign & testbed system integration integration Joachim Horwath (DLR) – responsible FSO experimentJoachim Horwath (DLR) – responsible FSO experimentMyles Capstik (University of York) – responsible RF experimentMyles Capstik (University of York) – responsible RF experiment

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High Altitude Systems:Constraints (1/2)

Operational environmentRarefied airLow temperatureHigh solar radiationWind streams

20°E, 60°N, July

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0 5 10 15 20 25 30 35 40 45 50 55 60

Wind speed [m/s]

Alt

itu

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[km

]

90% 99%Mean

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High Altitude Systems:Constraints (2/2)

Onboard devicesWeightPower ConsumptionHeat dissipationStabilised Pointing

Payload weight determines the volume of the Airship or the wing area

(therefore power) of the Airplane

Payload power needs determine the dimensioning of the power

supply system weight

Convective heat transfer nearly absent need for conductive

thermal bridges and/or irradiative solutionsIn case of directional device, a

real time Pointing-Acquisition-Tracking system shall be

available onboard, knowing the displacement of the target

Ground Station / User

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High Altitude Systems:Mission & System design (1/2)

REQUIREMENTS

Climb smoothly up to the low Stratosphere (>18500m)

Remain at high altitudeduring a 6h period,within a ground distance of 60km from the Ground Station,with high stability (pendulum effect < 1° amplitude)clear sky (good line of sight between the nacelle and the ground station)

Provide the proper support to the two onboard experiments, requiring a free cone of view, nadir pointing, each 140° solid angle aperture

Provide the proper power supply to the onboard experiments during the scheduled period

Provide the proper data links between the experiments onboard and the ground stations, for real time GPS acquisition and TM/TC service

Descent smoothly for payloads recovery

Land safely without injuring the payloads

Recover all the equipment at the launch base

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SOLUTIONS

Stratospheric Carrier System lifted by a 12000m3 Helium Balloon, after dynamic launch procedure

The Carrier is ‘piloted’ by means of a Ballast System and a Gas Release Valve on the balloon, in order to control the ascent speed and the floating altitude within the wind stream layers

Multi-payload Nacelle, designed around the payloads configuration

Electric Power Supply system based on High efficiency Lithium-Thionyl Chloride (Li-SOCl2) primary batteries and military-standard converters. The EPS box was equipped with photovoltaic heating system, after admitting possible increased test duration

Integrated GPS & TM/TC system allowing real-time availability of X,Y,Z position at the ground stations plus transparent serial links between the aerial segment and the ground segment of the two experiments

Nacelle turning system, for 180° rotation before descent, aimed to protect the payloads at touch down

High Altitude Systems:Mission & System design (2/2)

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Stratospheric Carrier System

gas valve

balloon

GPS + beacon

cutter

parachute

TM/TC + GPS

ballast

radio beacon

radar transponder

radar reflector

connection plate

nacelle turner

integrated nacelle

strobe light

video systemX

70m long flight train connected

to the Balloon

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SOLUTIONS

Stratospheric Carrier System lifted by a 12000m3 Helium Balloon, after dynamic launch procedure

The Carrier is ‘piloted’ by means of a Ballast System and a Gas Release Valve on the balloon, in order to control the ascent speed and the floating altitude within the wind stream layers

Multi-payload Nacelle, designed around the payloads configuration

Electric Power Supply system based on High efficiency Lithium-Thionyl Chloride (Li-SOCl2) primary batteries and military-standard converters. The EPS box was equipped with photovoltaic heating system, after admitting possible increased test duration

Integrated GPS & TM/TC system allowing real-time availability of X,Y,Z position at the ground stations plus transparent serial links between the aerial segment and the ground segment of the two experiments

Nacelle turning system, for 180° rotation before descent, aimed to protect the payloads at touch down

High Altitude Systems:Mission & System design (2/2)

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Multi-payload Nacelle

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SOLUTIONS

Stratospheric Carrier System lifted by a 12000m3 Helium Balloon, after dynamic launch procedure

The Carrier is ‘piloted’ by means of a Ballast System and a Gas Release Valve on the balloon, in order to control the ascent speed and the floating altitude within the wind stream layers

Multi-payload Nacelle, designed around the payloads configuration

Electric Power Supply system based on High efficiency Lithium-Thionyl Chloride (Li-SOCl2) primary batteries and military-standard converters. The EPS box was equipped with photovoltaic heating system, after admitting possible increased test duration

Integrated GPS & TM/TC system allowing real-time availability of X,Y,Z position at the ground stations plus transparent serial links between the aerial segment and the ground segment of the two experiments

Nacelle turning system, for 180° rotation before descent, aimed to protect the payloads at touch down

High Altitude Systems:Mission & System design (2/2)

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Electric Power Supply system

RUN 31: reduced power (50% - 65W) thermal insulation on RF PL & batteries

-70

-50

-30

-10

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70

90

0 1 2 3 4 5 6

time [hr]

tem

p [

°C]

T FSO_PL

T air inside POD

T POD skin IN

T POD skin OUT

T air outside POD

T RF_PL

T air inside RF_PL

T RF_POD skin IN

T RF-POD skin OUT

T battery 1

T battery 2

T battery 3

With average 20W heating power at altitude, the

battery box stabilised at a regime temperature of +37°C, optimising the

output efficiency

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SOLUTIONS

Stratospheric Carrier System lifted by a 12000m3 Helium Balloon, after dynamic launch procedure

The Carrier is ‘piloted’ by means of a Ballast System and a Gas Release Valve on the balloon, in order to control the ascent speed and the floating altitude within the wind stream layers

Multi-payload Nacelle, designed around the payloads configuration

Electric Power Supply system based on High efficiency Lithium-Thionyl Chloride (Li-SOCl2) primary batteries and military-standard converters. The EPS box was equipped with photovoltaic heating system, after admitting possible increased test duration

Integrated GPS & TM/TC system allowing real-time availability of X,Y,Z position at the ground stations plus transparent serial links between the aerial segment and the ground segment of the two experiments

Nacelle turning system, for 180° rotation before descent, aimed to protect the payloads at touch down

High Altitude Systems:Mission & System design (2/2)

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Integrated GPS & TM/TC Unit

GPS data provided real time at GS Data stream provided via LAN (IP) to the experiment ground stationsData stream provided according to NMEA-0183 standard

Transparent RS422 linkThree full duplex, asynchronous, transparent serial connectionsEach line will go through a RF line (nominal 402.2 MHz, Frequency Modulation) guaranteed a BER end-to-end better than 10^-5

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SOLUTIONS

Stratospheric Carrier System lifted by a 12000m3 Helium Balloon, after dynamic launch procedure

The Carrier is ‘piloted’ by means of a Ballast System and a Gas Release Valve on the balloon, in order to control the ascent speed and the floating altitude within the wind stream layers

Multi-payload Nacelle, designed around the payloads configuration

Electric Power Supply system based on High efficiency Lithium-Thionyl Chloride (Li-SOCl2) primary batteries and military-standard converters. The EPS box was equipped with photovoltaic heating system, after admitting possible increased test duration

Integrated GPS & TM/TC system allowing real-time availability of X,Y,Z position at the ground stations plus transparent serial links between the aerial segment and the ground segment of the two experiments

Nacelle turning system, for 180° rotation before descent, aimed to protect the payloads at touch down

High Altitude Systems:Mission & System design (2/2)

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Nacelle Turning System

Flight configuration

Pyro Cutter

Mockup for in-flight tests

Turned and landed - Measured 4g at secondary belt loading

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Ordinary tests on the single elements of the flight train and I/F verification

Tests on the nacelle turning system at ground with verification of the dynamics and the shock loads

Tests on the dynamic launch procedure with the Hercules launch vehicle and the nacelle mock-up

Two stratospheric flights (29/06/05, 11/07/05) with the fully equipped flight train, smaller balloon, mock-up of the Nacelle, in order to test:

Dynamic launch procedure with the Hercules vehicleIntegrated TM/TC & GPSBalloon cutterNacelle turning at high altitude (two different procedures)Parachute descent

Pre-flight test campaign with the ready-to-fly system

Preparation activities:Preliminary tests on the Stratospheric Carrier

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Preparation activities:Assembly, Integration, Verification into Hangars

The ‘Cathedral’ hangar hosts the offices plus room for AIV activities on the Nacelle, the RF experiment, the FSO

experiment

The ‘Basilica’ hangar is for the Balloon, the Parachute, the turning system and the connector plates

The ‘Church’ hangar is for AIV of TM/TC system, electronic devices, ballast machine and gas release valve

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Preparation activities:Ground stations site preparation

Disposal of the Telescope mounts for FSO experiment and for RF experiment

Disposal of Huts and tents for equipment and personnel for the two experiments

Power and data cabling of the positions for experiments

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Preparation activities:Meteorological survey (1/2)

Meteorological Breefing every morning

•Cloud coverage & possible precipitation

•Wind speed at ground

•Temperature at ground

•Wind profile up to 30km altitude

•Pressure, Temperature, Humidity up to 30km altitude

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Preparation activities:Meteorological survey (2/2)

Meteorological Breefing every morning

Foreseen flight path (ascent, float, descent)

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RF Experiment

Myles Capstik (UNY)

Experiments:Testbed design, implementation and preparation

FSO Experiment

Joachim Horwath (DLR)

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Preparation activities:Launch Pad

•Disposal of Helium Tanks and Balloon inflating system

•Disposal of Balloon release system

•Disposal of protection stripe for balloon, parachute and flight train development

•Disposal of light and power generators

•Disposal of check equipment for the elements of the flight train, at proper stations

•Disposal of the Wind indicator @ 100m altitude

•Definition and preparation of the 4 hours countdown operations list

•Tracing of the safety operation areas (laser safety)

•Nacelle installation on the Hercules vehicle

•Connection of the full flight train

•Mechanical, electrical and data connections check

•Payload functioning check

•Nacelle battery connection

•Balloon inflation

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Balloon Launch

FILM

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Flight Mission

01:52 Take off 03:16 Start piloting, Heading 114, Speed

5m/s, Horizontal distance 48.4km

03:06 Float stabilised at 24260m, Heading 100, Speed

5m/s

05:03 flying back, Altitude

23780m, Heading 218,

Horizontal distance 59.5km

10:18 Drop the remaining ballast,

Disarm the load sensor, Turn the Nacelle

10:19 Open the gas valve, Arm the flight termination device, Release the balloon

10:55 Nacelle impact,

67°28.595’ N, 21°25.961’ E

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RF Experiment

Myles Capstik (UNY)

Experiments:Operation and Results

FSO Experiment

Joachim Horwath (DLR)

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Conclusion