WATTS INNOVATIONS PRISM R.P.A.S., Flight Manual

Page: 46 / 141

PRISM FLIGHT MANUAL
46
This process allows users to easily replace a particular propulsion system in the event that
damage has occurred, as well as swap out entire propulsion systems when the scope of
the operation has changed. This technology allows a user to completely change out the
propulsion system all together without the need to ever press a single button or change
a single configuration. This is all done automatically within PRISM’s onboard computing
software.
The WattsQGC Application on the EchoSky Mobile includes a system status screen to
verify the mounting location, functionality, and individual flight time of each propulsion
boom system. This can be seen in the PRISM menu of the WattsQGC application.
PRISM uses 2x 12 cell LiPo batteries for flight. It is imperative that both batteries are of the
same specification, and have a similar amount of charge/discharge cycles. For this reason,
the 2 batteries that make up a single flight pack should be kept as a matching set. Unless
1 battery fails or begins to underperform, the flight pack should not be split up.
More details about the use of batteries, as well as maintenance and care are provided in
Chapter 3
.
Power from the flight packs is connected by the main power plugs to a central power
distribution board. This PDB is rated to 400 amps continuous power input. Each arm socket
is rated to 100A continuous current each, but the maximum amount of amperage draw as
seen from the most power hungry propulsion system is not even half of that. This 2:1 ratio
allows the user to fly confidently, knowing that the electrical system can handle extreme
power loads.
The Flight controller is powered directly from the flight batteries through two individual
5V Regulator systems. These regulator systems are completely separate, which allows
redundancy in the event that one fails in flight.
Each of the U8ii propulsion units are connected directly to the PDB and receive power
directly from the Flight Batteries through the small spring loaded pins. These pins allow
power, data, and motor PWM to be carried from the propulsion system up to the Cube. All
data connections, PWM signals, and power are configured in a redundant manner, meaning
that a multitude of pins can fail and the aircraft will stay airborne.
Voltage and current draw information is calculated by two current sensors installed
between the power distribution board and the battery packs. (See Figure 6 for a
wiring schematic). This allows the aircraft to be able to read current from both
batteries individually. Voltage however is always averaged between the two
batteries.
7.6 FLIGHT BATTERY
7.7 ELECTRICAL SYSTEMS