f . T h e ambient temperature of the simulator compartment and the cockpit is
c o n t r o l l e d by adjusting the thermostat located on the back wall of the compart-
ment. C o n d i t i o n e d air is ducted through the compartment area and the normal
h e l i c o p t e r cockpit heating and defrosting ducts. T h e cockpit environment control
s y s t e m switches and controls are nonfunctional.
g. A platform step is provided alongside each cockpit to facilitate entrance and
e x i t . L o w - l e v e l step lighting is provided for safety and is a function of the
The instructor/operator stations (IOS) are
2 - 3 . INSTRUCTOR/ OPERATOR STATIONS.
l o c a t e d adjacent and to the rear of the cockpit In each simulator compartment.
( R e f e r to Section II for further details.) The IOS allows instructors/operators to
c o n t r o l the training program and effectively monitor and evaluate trainee perform-
ance . D u r i n g training, t h e pilot and CPG IOS function in either independent or
i n t e g r a t e d modes of operation.
2 - 4 . MOTION SYSTEM. E a c h simulator compartment is mounted on a six-degree-of-
freedom (6-DOF) motion system consisting of a moving platform assembly driven and
s u p p o r t e d from below by six identical hydraulic actuators. The motion system is
c a p a b l e of providing cues for pitch, roll, yaw, lateral, longitudinal, and vertical
movements. System motion can be either Independent (without simultaneous motion in
a n y other degree of freedom) or in any combination desired to produce real-time
dynamic motion cues.
a . F l i g h t simulation includes combined motion representing changes in aircraft
attitude as a direct result of flight controls, rough air, and wind, and changes in
a i r c r a f t weight and center-of-gravity resulting from fuel consumption or weapon and
a m m u n i t i o n depletion. A l s o , motion effects such as droop-stop pounding, blade
s t a l l , b l a d e i m b a l a n c e , d a m p e r f a i l u r e , b l a d e s out-of-track, and touchdown impact
can be produced.
b . T h e computer-controlled simulation program causes the motion system to re-
s p o n d realistically to aerodynamic forces and moments within the mechanical limits
o f the system. A l l motions except pitch are imperceptibly washed out to the
n e u t r a l position after the computed accelerations have reached zero. P i t c h
a t t i t u d e is maintained as necessary to simulate sustained longitudinal acceleration
cues. Acceleration onset cues are scaled as large as possible to fully utilize the
r a n g e of motion capabilities of each degree-of-freedom.
c . Depending on the particular flight program, t h e motion system responds to
c o m p u t e r input signals as noted in the following examples:
( 1 ) Ground conditions. T h e motion system provides the vibrational indications
a p p r o p r i a t e t o m o t i o n o f t h e a i r c r a f t d u r i n g s t a r t u p . The system produces a random,
l o w - f r e q u e n c y , low-amplitude. multidirectional oscillation with reasonably abrupt
a p p l i c a t i o n . T h e computer simulation program varies the amplitude of oscillation
to reproduce the irregularities of less than ideal flight takeoff conditions.
( 2 ) Takeoff and landing. T h e motion system provides simulated realistic
effects for all forms of takeoff, flight, and landing conditions.