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This report describes a series of flying qualities investigations designed to look at flying qualities
issues associated with fly-by-wire control laws for civil transport aircraft. It follows on from a
previous study which considered flying qualities for the reconfiguration, approach and landing
tasks. Issues raised during this previous study were followed up and design improvements made
to the control laws in order t o improve them for this subsequent series of evaluations.
Two different tasks are considered for this series of evaluations for the following reasons. Firstly,
the control laws were only evaluated between airspeeds of 140 knots and 121 knots for the approach
and then to approximately 115 knots in the flare during the previous set of evaluations. This
obviously does not cover the entire aircraft airspeed range, but since the approach and landing task
is generally accepted t o be the most critical task for a civil aircraft, it is deemed a suitable task for
evaluating the control laws under consideration.
However, civil aircraft manufacturers generally use other tasks for the evaluation of control laws
since there is a requirement t o test the laws over the full flight envelope. For example, several
different tasks were used for evaluation during the design of the Boeing 777, including a variety of
approach tasks, en-route tasks, and in-flight tracking type tasks.
A formation flying task was therefore proposed as a suitable task for evaluating control law performance at altitude for the generic regional aircraft. It was initially thought t o be a tight flight path
control task, and this was quickly confirmed from a brief trial prior t o the main evaluations. In
addition, this task is one which is the most demanding for a large military aircraft since it requires
precision control of both flight path and airspeed. Finally, it is becoming more and more common
to use modified civil aircraft in either the military transport or in-flight refuelling roles, with the
Vickers VC-10 and Lockheed L-1101 being used as in-flight refuelling receivers and tankers and the
Nimrod (Military Comet) as a receiver in the Royal Air Force alone.
It was also decided t o consider atmospheric effects. Initially, it was proposed t o consider the effects
of both windshear and turbulence, but evaluations in turbulent conditions were later dropped since
its main effect is in the longitudinal (airspeed) axis, with effects in the longitudinal (pitch) axis
being limited by the effects of the control laws. In addition it did not give repeatable results.
However windshear, which here is taken to represent a decreasing headwind, is a flight path control problem since it causes an effective change in aircraft flight path angle, and it was found to be a much more suitable task. |
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