VIA Technologies EPIA SN-Series Specifications Page 71

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FASTER Engineering Model
59
Despite these requirement relaxations, the result is compliant with the initial idea of a
functioning test bed able to guarantee sufficient performances in order gain experience in
the process of realization of the final system.
In order to proceed to the definition of the system, a functional block diagram of the
airborne internal management and computing system has been drawn and is shown in
Figure 50. The unit is managed by the Data Acquisition and Camera Timing block which
receives position and attitude data respectively from the G.P.S receiver and the Inertial
Measurement Unit. The camera arm switch controls the image acquisition mode and is
activated by the pilot once overflying the target area. If the camera switch is armed the
unit sends to the acquisition devices an appropriate electric signal controlling the shooting
mode. The entire flight plan (list of 3-Dimensional waypoints) is loaded before flight
directly from the ground segment infrastructure, using the flight planner described in
Chapter 4.
The flight plan is presented to the pilot using the “tunnel in the sky” visual interface,
which through a geometrical interpolation of the reference waypoints, displays the pre-
computed trajectory.
Data Acquisition Unit &
Camera Timing
G.P.S
Receiver
I.M.U
Camera Arm
Switch
Pilot Visual
Interface
Camera
Parameters
Controller &
Storage
Camera
Flight Plan
Pilot
Shoot Control
Data Download (images)
Camera Setup
Position
Attitude
On Target Camera Arm Signal
Pilot I/F Data
Ancillary Data
Ground Segment
Georeferenced
data
Camera Computed
Setup
Flight Plan Management
Figure 50: Airborne internal management and computing system functional layout
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