초록 ▼

A control system for providing individual blade control inputs to a four-bladed helicopter rotor. Limited authority series actuators located in a non-rotating portion of the helicopter are driven by a computer which receives inputs from individual blade sensors and aircraft stabilization sensors, su

A control system for providing individual blade control inputs to a four-bladed helicopter rotor. Limited authority series actuators located in a non-rotating portion of the helicopter are driven by a computer which receives inputs from individual blade sensors and aircraft stabilization sensors, summed with cockpit control inputs, and the resultant motions transmitted to the rotor blades through a conventional swashplate which drives four blades of the rotor and a translatable differential sleeve and summing linkage which drives only two blades. The differential sleeve is adapted for axially raising or lowering the swashplate. The combined motion of swashplate and differential sleeve is shown mathematically to result in individual blade control in pitch. Computer individual blade commands are converted from the rotating reference frame to cyclic, collective and differential blade pitch commands in the fixed reference frame through a coordinate transformation matrix.

대표청구항 ▼

An individual blade control system for a helicopter having a variable pitch sustaining rotor with at least four substantially horizontally disposed blades, comprising: a substantially vertical shaft supporting said rotor and having first and second radially extended members flexibly coupled to oppos

An individual blade control system for a helicopter having a variable pitch sustaining rotor with at least four substantially horizontally disposed blades, comprising: a substantially vertical shaft supporting said rotor and having first and second radially extended members flexibly coupled to opposing first and second ones of said rotor blades, respectively, differential sleeve means slideably mounted for rotation and axial displacement with respect to a longtitudinal axis of said vertical shaft and having third and fourth radially extended members flexibly coupled to opposing third and fourth ones of said rotor blades, respectively, and orthogonal to said first and second radially extended members, servo actuator means, responsive to a first control signal, and operably coupled to raise or lower said differential sleeve with respect to said vertical shaft, swashplate means, mounted for rotation about said vertical shaft and having a first pair of radially extended members flexibly coupled to corresponding ones of said first and second members of said vertical shaft and a second pair of radially extended members flexibly coupled to corresponding ones of said third and fourth differential sleeve members, swashplate support means in the form of an annular member slideably engaging said swashplate means and mounted for axial displacement along said shaft, said support means adapted for oblique displacement with respect to said longitudinal axis of said shaft, and having a plurality of radially extended members operably coupled to ones of a corresponding plurality of further servo actuator means, said plurality of further servo actuator means responsive to control mixer means, means for applying a first control signal in accordance with a predetermined pitch control law to said servo actuator means, and means for applying second control signals in accordance with said predetermined pitch control law to said plurality of further servo actuator means, whereby ones of said rotor blades are selectively feathered to a predetermined pitch angle at a predetermined azimuth with respect to the heading of said helicopter in accordance with deflections of said differential sleeve means and said swashplate.