The application for this control loader system is for rotary and fixed wing aircraft, but can be adapted for a variety of training simulation apparatus. Utilizing minimal to zero backlash gearboxes in a variety of configurations in conjunction with DC brush type motors, friction and inertia are virtually removed from the system and are not present in the flight controls. Price available upon request.
Based on modified Helical gearboxes (<1arcrad) or custom made zero backlash (0 acrrad) belt drive systems, these control loader systems make for the highest performance, unmatched smoothness and stable servo with minimum maintenance requirements, ease of installation and longevity that is in the decades. The electronics for this system are modular in nature and are modified COTS items.
The aircraft control model is based on real aircraft data model. Any type of control system can be simulated: fully boosted, partially boosted or non-boosted. The spring rate and the damping can be varied so that the system can simulate the change in the force gradient and damping that is present with the change in dynamic pressure.
Friction, stops, breakouts, boost actuators, non-linear gearing, non-linear hinge moments and auto-pilots (simulated and real) are available with this system.
For aircraft that have separate left and right controls, separate actuators can be utilized and the controls can be linked via software.
Several interfaces are available: Bit 3, Ethernet, DR-11W (Concurrent), HSD (Encore), and UBC (Universal Bus Controller, Harris). Bit 3 is the easiest to use, Ethernet is the lowest cost for hardware. RS-232 can be used but is usually too slow. DR-11W, HSD, and UBC are essentially obsolete and should only be used with older host computers.
Coupled mass system. Model includes cable spring, coupled mass, friction, damping, aero hinge moment, aero damping, boost actuators, non-linear gearing, breakout, centering spring, for and aft stops (fixed or movable), trim, autopilot engage, weight on nose wheel, nose wheel velocity and nose wheel velocity angle.
Dynamic pressure, roll rate, pitch rate, yaw rate, dynamic pressure divided by velocity, boost oil pressure, autopilot command, autopilot engage, weight on nose wheel, nose wheel velocity and nose wheel angle.
Stick positions, Pedal position, Surface positions, control forces, nose wheel angle, nose wheel force, error code.
115 (230) volts, 7 (3.5) amps peak per axis
115 (230) volts, 1 (0.5) amps quiescent per axis
115 (230) volts, 3 (1.5) amps for the processor