Transcript Blank Presentation

Bruxelles 9.03.06
CAPANINA Trial 2
Wireless and optical broadband technologies from HAPs
Kiruna/ESRANGE Sweden, 30.8.2005
Marco Bobbio Pallavicini, Myles Capstick, Joachim Horwath
1
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
2
Capanina Network
Concept
31/28GHz, (<11GHz),
+ optical backhaul and interplatform
Fixed BFWA particularly
for rural locations
Up to 120Mbit/s
symmetric links
17-22km
Steerable/
Smart Antenna
WLAN
Moving Train
Up to 300km/h
To be validated:
RF link: stratospheric node - ground node
FSO link: stratospheric node - ground node
3
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 1 : Low altitude test, by
means of Tethered Balloon
Summer 2004, Pershore, UK
Trial 2 : High altitude test, by
means of Stratospheric
Balloon
Summer 2005, Kiruna, S
Trial 3 : High altitude test, by
means of Stratospheric
Airplane
Summer 2006, Kawai/Edwards TBC
Demonstration of a reduced
network with FSO
communication within two
flying platforms
2007
TBD
Marco Bobbio Pallavicini – responsible test campaign & testbed system integration
Joachim Horwath (DLR) – responsible FSO experiment
Myles Capstik (University of York) – responsible RF experiment
4
High Altitude Systems:
Constraints (1/2)
20°E, 60°N , Ju ly
Operational environment
26
90%
M e an
99%
24
22
20
18
A ltitu d e [km ]
Rarefied air
Low temperature
High solar radiation
Wind streams
16
14
12
10
8
6
4
2
0
0
5
10
15
20
25
30
35
W in d sp e e d [m /s]
5
40
45
50
55
60
High Altitude Systems:
Constraints (2/2)
Payload weight determines the volume
of the Airship or the wing area
(therefore power) of the Airplane
Onboard devices
Weight
Power Consumption
Heat dissipation
Stabilised Pointing
In case of directional device, a
real time Pointing-AcquisitionTracking system shall be
available onboard, knowing the
displacement of the target
Ground Station / User
6
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 solutions
High Altitude Systems:
Mission & System design (1/2)
REQUIREMENTS
Climb smoothly up to the low Stratosphere (>18500m)
Remain at high altitude
during 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
7
High Altitude Systems:
Mission & System design (2/2)
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
8
Stratospheric
Carrier System
gas valve
balloon
GPS + beacon
cutter
parachute
TM/TC + GPS
ballast
radio beacon
radar transponder
strobe light
radar reflector
X
video system
connection plate
nacelle turner
integrated nacelle
9
70m long
flight train
connected
to the
Balloon
High Altitude Systems:
Mission & System design (2/2)
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
10
Multi-payload
Nacelle
11
High Altitude Systems:
Mission & System design (2/2)
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
12
Electric Power
Supply system
RUN 31: reduced power (50% - 65W)
therm al insulation on RF PL & batteries
T FSO_PL
T air inside POD
T POD skin IN
temp [°C]
90
70
T POD skin OUT
50
T air outside POD
30
T RF_PL
10
T air inside RF_PL
-10
-30
0
1
2
3
4
6
T RF_POD skin IN
T RF-POD skin OUT
-50
T battery 1
-70
time [hr]
With average 20W heating
power at altitude, the
battery box stabilised at a
regime temperature of
+37°C, optimising the
output efficiency
13
5
T battery 2
T battery 3
High Altitude Systems:
Mission & System design (2/2)
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
14
Integrated GPS &
TM/TC Unit
GPS data provided real time at GS
Data stream provided via LAN (IP) to the
experiment ground stations
Data stream provided according to NMEA-0183
standard
Transparent RS422 link
Three full duplex, asynchronous, transparent
serial connections
Each line will go through a RF line (nominal
402.2 MHz, Frequency Modulation) 
guaranteed a BER end-to-end
better
than 10^-5
15
High Altitude Systems:
Mission & System design (2/2)
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
16
Nacelle Turning
System
Pyro Cutter
Flight configuration
Mockup for in-flight tests
Turned and landed - Measured 4g at secondary belt loading
17
Preparation activities:
Preliminary tests on the Stratospheric Carrier
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 vehicle
Integrated TM/TC & GPS
Balloon cutter
Nacelle turning at high altitude (two different
procedures)
Parachute descent
Pre-flight test campaign with the ready-to-fly
system
18
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
19
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
20
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
21
Preparation activities:
Meteorological survey (2/2)
Meteorological Breefing every morning
Foreseen flight path (ascent, float, descent)
22
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
23
Marco: The Launch
Film ??
24
Flight Mission
01:52 Take off
03:06 Float stabilised at 24260m,
Heading 100, Speed 5m/s
03:16 Start piloting,
Heading 114, Speed 5m/s,
Horizontal distance 48.4km
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
25
10:55 Nacelle
impact, 67°28.595’
N, 21°25.961’ E