We acquired and AS-500 model from the english company Airspeed
Airships. Criteria for this choice were the size of the blimp (which
we wanted to be rather small, for the ease of deployment and stocking),
its available payload and its possible operation modes.
Nominal specifications According to the constructor, the
technical characteristics of the original AS-500 model are the following:
- 7.8 m long, 1.80 m max diameter, giving a volume of about
15.0 m³, and a fitness ratio of 4.25.
- Vectorized thrust (100° range), with two
7.5 cm³ engines, allowing speeds up to 45 km/h, possible
control in wind gusts up to 25 km/h, and an endurance of 40 minutes
with a 1.0 kg fuel load.
- The hull is made of welded mylar, and equipped with 4 control
rudders in a ``X shape'' configuration. A ballonet fed with air captured
at the rear of the propellers maintains a constant hull pressure, and a
radio-controlled valve on top of the hull can release helium when the
temperature is getting higher.
- The static payload of the AS-500 ( i.e to reach the
equilibrium) is 3.5 kg, and the blimp must always be
overweighted of 1.5 to 2.0 kg in flight: the maximal available
payload is therefore about 5 kg.
Specific modifications In collaboration with Airspeed Airships,
we specified the following modifications for our purpose:
- Electric motors: to have a finer controllability, we preferred to
opt for electric motors. They do not weigh more than fuel engines, but
are less powerful, thus reducing the maximum reachable speed and the
possibility to fly in wind gusts. Their main drawback is the weight of
the required batteries, which considerably reduces the available
payload. However, thanks to lighter batteries and possible alternative
energy sources, this drawback can be overcomed.
- Stern thruster: the rudder control surfaces require a certain
speed to allow changes in both the altitude and orientation of the
blimp. In order to have the possibility to maneuver the blimp while
hovering, we choose to add a stern thruster, that gives the
possibility to control the yaw angle.
The various controls available on the blimp
On-board equipment
To transform the blimp from a radio-controlled machine to a robot, we
are currently equipping it with a set of proprioceptive and
exteroceptive sensors, and with computing and communications
capabilities.
- Stereovision One of the advantage of having a big platform
is that it can carry a wide base stereo bench, thus having the
possibility to directly gather 3D data on the overflown ground. We
adapted 2 high resolution digital B&W cameras on a rigid 2 m
carbon profile that traverses the 1.4 m long AS-500 gondola (use of
stereo imagery to build a high resolution DEM is presented here).
- Blimp state observation In order to tackle the flight
control problem (and also to ease the development of mapping
algorithms), we added the following sensors: a differential GPS
receiver, a fluxgate compass, that also provide the blimp pitch and roll
angles, and a wind sensor (sonar transducer technology), that measures
the speed and orientation of the relative wind in the longitudinal
plane.
- CPU We opted for a Matrox 4Sight board: it is an
EBX form factor PC motherboard, endowed with all the necessary
communication ports (100base-T ethernet, two USB ports, two RS232 ports,
16 TTLs, and especially 3 firewire ports). The board comprises a PC104
slot, on which we added four more RS232 ports and a PCMCIA interface to
host a light 11 Mbits/s ethernet modem card. Thanks to the 566 Mhz
Celeron processor, vision algorithms will eventually run on-board the
CPU.
- Actuator control The control surfaces and motor servos of
the blimp are usual PWM controlled modelist devices. We use a single
chip (a FerretTronics FT629) that can generate up to 8 sustained PWM
signals from a RS232 input to control the actuators. For safety reasons,
it is essential that an operator can retrieve the blimp control from the
ground with the radio, at anytime: this is done thanks to a radio
controlled switch, that cuts the PWM signals coming out from the chip.
The whole hardware architecture is sketched in the figure below, and
some specifications of the various devices are summarized in the
following table. The total equipment weight is 1.520 kg, which
leaves only 1.300 kg for the various mechanical parts, wires and
batteries that must provide the necessary additional 40 W.
Schematic view of the on-board equipment
Device |
Brand/model |
Weight (g) |
Power requirements (x Watts @ y Volts) |
Comments |
Compass / Inclinometer |
Precision Nav. / TCM2 |
30 g |
0.25 W @ 12 V |
yaw : 1.0° RMS; Pitch/Roll : 0.2°
RMS |
Wind sensor |
LCJ Capteurs / CV3F |
240 g |
0.6 W @ 12 V |
Acc.: 0.05 m/s, 1.5° |
GPS |
Trimble / Lassen SK II |
110 g |
2.0 W @ 5 V |
Acc.: 2 m CEP, 0.05 m/s |
Stereo Cameras |
Vitana/PL-A633 |
2 x 80 g |
2 x 3 W @ 12 V |
1280 x 1024 B&W images, 10 bits pixels |
Lenses |
Cosmicar / 12mm F 1.2 |
2 x 65 g |
|
36° x 45° field of view |
CPU |
Matrox/4Sight |
850 g |
30 W @ 12 V |
Including 2 PC104 boards, 20 Go HD, modem |
Total |
|
1.520 kg |
< 40 W @ 12 V |
|
Characteristics of the on-board equipment
Energy management
Energy is a critical issue for any flying device, mainly for safety
considerations. In our case, we also would like to have more autonomy,
while satisfying the maximal payload constraint.
Our AS-500 was originally equipped with 3 sets of NiCd batteries: one
for the radio receiver and the servos (4.8 V, 1.2 Ah,
0.140 kg), one for the stern thruster (7.2 V, 2.0 Ah,
0.350 kg) and one for the main thrusters (14.4 v, 5.0 Ah,
1.880 kg).
We decided to replace the two thruster batteries with Lithium/Ion
batteries, that have a much more interesting power/weight ratio (about
2.5 times better, which respectively saves 1.200 kg and 0.200 kg
weight for the main and stern thrusters), and to feed the instruments
with an other separate set of batteries. In total, the blimp now has 4
power sources, each of them being critical for its operation. So each
battery is managed by a Maxim MAX1648 chip, that allows both the
``intelligent'' charge of the battery and the dispatching of status
informations to the CPU via a multiplexed serial link. The four charging
modules are linked to a single connector, on which a power source is
plugged while the blimp is on the ground (which allows booting and
debugging without any power loss), and on which a rescue set of non
rechargeable Lithium/Ion batteries is plugged in flight (an additional
weight of only 0.200 kg to deliver 5.0 Ah @ 15 V). This very
flexible structure also allows the future use of an alternate power
source on flight, such as a Stirling engine of a fuel cell.
Current status
At the date of Feb the 15th 2002, the whole equipment mechanical
integration is under way. All the on-board added equipment (besides the
stereo bench and the wind sensor, which is mounted on the nose of the
blimp) fits into a drawer-like box that can be easily removed from the
gondola. The following additional devices are considered:
More sensors
The various blimp state estimation sensors mentioned above provide the
sufficient informations to tackle flight control in aerostatic mode
(i.e. hovering or flying at very low speeds). But to control
aerodynamic modes, the pitch and yaw rate informations are necessary. We
do not know whether the derivation of these informations from the
inclinometers will be suitable or not: if not, we will add two
solid-state rate gyros for that purpose. Also, the altitude estimate
provided by the GPS receiver is not precise enough to safely servo the
taking-off and landing phases: for that purpose, we will add a sonar
telemeter. Fortunately, the main drawback of sonars in robotics,
i.e. their wide perception cone which make their data
interpretation so tedious, will turn into an advantage in our case, as
there will be no need to mechanically stabilize it along the
vertical. Finally, we are still investigating for a 3D wind sensor
(Pitot tubes are unfortunately not sensitive enough at the low blimp
speeds).
Energy issues
As mentioned above, energy is a critical issue for a blimp. In our case,
the square/cube law deters the use of solar cells (an airship surface
grows up with the square of its dimension, whereas its volume grows up
with the cube. This has important consequences on airship
controllability in wind gusts, the aerodynamic forces and the inertia
being respectively proportional to the square and the cube, but also on
the possibility to use solar cells). A very appealing solution would be
to use a Stirling engine, that could provide a large autonomy: we are
currently investigating to find an engine that would deliver a few tens
of Watts. Our choice of energy management can easily benefit from such a
device, which output would simply be plugged to the main connector. The
batteries will be kept, to ensure the possibility to deliver high energy
when required (during taking-off for instance).
Sara Fleury, Matthieu Herrb, Simon Lacroix, Xavier "steelfingers" Dollat, Patrick "goldfingers" Marcoul, Arnaud Jacquet.
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General Information
Robots
Rovers Navigation
Autonomous Blimps
Multi-Robot Cooperation
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